JPH09303994A - Flying member - Google Patents

Abstract

PROBLEM TO BE SOLVED: To obtain a stable falling state and normally operate a payload by providing a relatively small parachute area in a parachute unit, opening a stable parachute simultaneously with the separation of the parachute and opening a main parachute after a prescribed time. SOLUTION: In a flying member flying, and falling by discharging a parachute 2 at a prescribed time after it is shot, the payload 1 is located in the front part of the flying member and the parachute 2 is housed in the flying member just after it is shot and connected to the payload 1 through a sling. Then, a separator 8 is provided for connecting a stable parachute 7 to a plate located in the rear part of the parachute 2 through a sling and separating the stable parachute 7 after a prescribed time. The payload 1 stably flies under inertia by virtue of the operation of the expanded stable parachute 7 and reduces its speed under the air resistance of the stable parachute 7. Then, the stable parachute separator 8 operates to separate the stable parachute 7 and discharge the parachute 2 at the same time.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention improves the attitude stability of a payload of a flying object that is launched from the ground or on a ship and releases a parachute after a certain period of time and floats down by the parachute, and The present invention relates to improvement in operational reliability of devices in a payload by reducing impact when opening an umbrella.

[0002]

2. Description of the Related Art A parachute is emitted from the ground or on board a ship after a certain period of time, and the parachute is emitted at an appropriate distance and altitude from the launching point. FIG. 5 shows a conventional example of a flying vehicle that fulfills a specific task. Figure 5 is an example of a projectile launched from the ship. In the figure, 15 is a conventional projectile, 16 is a surface ship, 17 is a guided projectile, and the arrow indicates the projectile 15 after launch. Indicates the flight route. When it detects that an attack by the guided flying body 17 has been made on the surface ship 16, it launches the flying body 15. The flying body 15 flies in the route shown in the figure, and when it reaches a predetermined altitude, it releases and deploys a built-in parachute, stably floating and descending, and emits radio waves and the like toward the guided flying body 17 in the meantime. The guide device of the guided flying body 17 is obstructed or deceived to obstruct the guidance to the surface ship 16 or to attract the flying body 15 itself to protect the surface ship 16.

In such a flying object, it is desired that the posture of the payload after the release of the parachute is stable and that the flight time is sufficiently long.

FIG. 6 is an explanatory view of a conventional flying body, FIG. 6 (a) is a perspective view showing the appearance, and FIG. 6 (b) is a sectional view showing the outline of the structure. In the figure, 1 is a payload, 2 is a parachute, 3 is a suspension line, 4 is a parachute unit for storing the parachute 2 and the suspension line 3, 5 is a propulsion device, and 6 is a stabilizing wing. Figure 7
FIG. 6 is an explanatory diagram of a conventional flying sequence of a flying object. FIG. 7A shows a state immediately after the launch, and the propulsion device 5 accelerates and rises. In this state, the flying body stably flies by the action of the stabilizing wings 6. FIG. 7B shows the state at the moment when the parachute unit 4 is separated by the separation mechanism, which is omitted in FIG. 6, when a predetermined time has elapsed. FIG.7 (c) is a state after the separation of the parachute unit 4 and the propulsion device 5 falls freely. Although the payload continues to fly inertially, the stability wings 6 are lost, so that the posture is likely to be unstable, and the payload may fall over in some cases. FIG. 7 (d)
The state at the moment when the parachute 2 is deployed is shown. At this point, the payload 1 is still high in speed, so that the aerodynamic load of the parachute 2 is large and the load applied to the suspension rope 3 is also large. FIG. 7 (e)
Shows that payload 1 is stabilized downwards,
If the parachute 2 or the suspension line 3 is damaged by an excessive aerodynamic load,
It will not be in a stable state, and the flight time will be insufficient.

[0005]

[Problems to be Solved by the Invention] It is important to secure a flight time for a flying vehicle operated as described above. To this end, use a parachute having a large umbrella area as much as possible. Is effective. However, when the umbrella body area of the parachute is increased, the aerodynamic load when the umbrella is opened increases. The aerodynamic load generated when the parachute is opened is given by the following equation.

[0006]

[Equation 1]

Where ρ is the air density, usually 0.12
Used 5kgfs ² / m ^4. υ is the speed of the flying object,
For C _D, a resistance coefficient of 0.68 is used. S is the umbrella area, N
Is an impact coefficient, and a value between 1 and 2 is usually used. The aerodynamic load generated at the time of opening the umbrella is, for example, about 10 ton when a flying object having a parachute with an umbrella body area of 12 m ² is opened at a speed of 150 m / s. Therefore, if twelve hoisting lines come out from the umbrella, each one will bear a load of 850 kgf, and even a high-strength Kevlar thread will have a diameter of 7
A ~ 8 mm suspension line is required. Furthermore, the attachment part of the suspension rope and the umbrella itself must also be able to withstand such a large load, and there is a problem that the entire flying body becomes large and heavy. Usually, the size and weight of the flying body are limited, so if a design with no allowance is made within the limits, aerodynamic loads will cause the suspension lines to break, the umbrella body to break, and the desired descent. There is a problem that the speed cannot be obtained and the flight time is insufficient. Further, even in the design of the electronic device in the payload, it is necessary to withstand the impact force due to this large aerodynamic load, which causes a problem of increasing cost and lowering operational reliability. In addition, after the parachute is released, in order for the device in the payload to normally act on the target, for example, the guided flying object, it is necessary to stabilize the posture and correctly orient to the target. As described above, if the parachute does not open properly due to cutting of the hanging rope, tearing of the umbrella body, etc., the posture of the payload will not be stable, and the electronic device in the payload will not work effectively against the target. there were.

The present invention has been made to solve such a problem. When opening a parachute, first open an umbrella having a small umbrella body area and gradually decelerate while keeping the posture of the payload stable. Let's (hereinafter, this umbrella is called a stable umbrella),
The purpose is to make the payload function normally by separating the stable umbrella and releasing the parachute at the same time after releasing the flying body to a speed at which the aerodynamic load becomes sufficiently small, and at the same time making the parachute in a stable descent state.

[0009]

A flying body according to the present invention has a stable umbrella having a relatively small umbrella area in a parachute unit, and when the aircraft separates, the stable umbrella opens.
The means for opening the main umbrella after a certain period of time is provided.

[0010]

In the present invention, the stable umbrella having a small area is first discharged when the parachute is discharged. At this time, the flying object has a high velocity but the umbrella area is small, so that the aerodynamic load is not large. Therefore, there is no problem such as breakage of the stabilizing umbrella, the suspension line, and the mounting portion. Therefore, the flying body continues stable flight. Also, the equipment in the payload is not subjected to excessive shock. Due to the resistance of the stabilizing umbrella, when the flying body slows down sufficiently, the stabilizing umbrella is separated and the parachute is ejected and extended. At this point, the flying body has slowed down sufficiently, so even if you deploy a parachute with a large umbrella area,
Aerodynamic load is small enough. Therefore, since there is no problem caused by an excessive aerodynamic load, the parachute can be normally extended and the payload can be moved to floating descent in a stable state.

[0011]

【Example】

Embodiment 1 FIG. 1 and 2 are explanatory views showing an embodiment of the present invention, FIG. 1 (a) is a perspective view, FIG. 1 (b) is a sectional view showing the outline of the structure, and FIG. 2 (a) is a stable umbrella. FIG. 2B is a cross-sectional view showing the outline of the structure when the stable umbrella is deployed, and FIG. In the figure, 7 is a stable umbrella, and 8 is a stable umbrella separating device. FIG. 3 is an explanatory diagram of the flight sequence of the embodiment of the present invention. FIG. 3 (a)
Is the state immediately after launch and is the same as a conventional flying object. FIG. 3B shows a state at the moment when the parachute unit 4 is separated, which is the same as the conventional flying body. Figure 3 (c)
Is a state in which the separation of the parachute unit is completed, the propulsion device 5 freely falls, and the stable umbrella 7 is released. FIG. 3 (d)
Is a state in which the payload 1 is flying by inertia, and the payload 1 stably flies by the action of the deployed stabilizing umbrella 7, and at the same time decelerates by the air resistance of the stabilizing umbrella. In FIG. 3E, the stable umbrella separating device 8 is activated and the stable umbrella 7 is operated.
Shows the state in which the parachute 2 is released at the same time when the parachute 2 is separated. At this time, since the payload 1 is sufficiently decelerated, even if the parachute 2 is extended, the aerodynamic load is small, and the problems such as the breakage of the umbrella body, the disconnection of the suspension line, and the damage of the electronic device do not occur. FIG.
(F) is a state in which the parachute has completed the extension and is descending stably. Since the parachute 2 opens normally without damage, the posture of the payload 1 stabilizes promptly, and at the same time the desired airborne time can be secured, and the equipment of the payload 1 also functions normally, aiming for the target. Works effectively.

FIG. 4 is a sectional view for explaining the details of the stable umbrella separating device 8 according to the embodiment of the present invention. FIG. 4 (a) is a state of operation of the stable umbrella separating device 8, and FIG. 4 (b) is. The state after operation is shown. In the figure, 9 is a plate, 10 is a C ring, 11 is a slider, 12 is an actuator, 13 is a groove, and 14 is a trigger pin. Simultaneously with the development of the stable umbrella, the trigger pin 14 comes off due to the aerodynamic load, and the actuator 12 is triggered.

The flying umbrella stabilizing device 8 according to the present invention is in the state shown in FIG. 4 (a) up to the state shown in FIG. 3 (d). Although the outer diameter of the C ring 10 in the free state is smaller than the inner diameter of the groove 13 on the inner surface of the outer cylinder of the flying body,
In the state of (a), the C ring 10 is stretched so that the outer diameter is changed to the groove 13.
It is inserted into the groove 13 by making it larger than the inner diameter.
Further, the C ring 10 tries to return to the free state by the spring force, but the slider 11 is inserted into the notch of the C ring 10 to prevent this movement. The slider 11 is the plate 9
It is connected to the actuator 12 which is fixed by screws or the like. In this state, since the plate 9 is fixed to the outer cylinder of the flying body via the C ring 10, the plate 9 is kept in the state of being coupled to the plate 9. Further, the area of the fit between the C ring 10 and the groove 13 bears the aerodynamic load of the stabilizing umbrella 7, which is structurally advantageous. When the payload 1 is sufficiently decelerated, the actuator 12 which has been operated for a predetermined time after the trigger is applied is activated to move the slider 11 in the direction of the arrow (A). When the slider 11 moves and comes out of the notch of the C ring 10, the spring force of the C ring 10 returns the C ring 10 to the free state. Free state C ring 1
Since the outer diameter of 0 is smaller than the inner diameter of the groove 13, the C ring 10
Is disengaged from the groove 13 and the plate 9 is separated from the outer cylinder of the flying body. The plate 9 is connected to the stabilizing umbrella 7 and is quickly separated from the payload 1 by the air resistance of the stabilizing umbrella 7. It should be noted that the drive source of the actuator 12 may be any one that has a sufficient drive force, such as explosive powder or a solenoid. When the plate 9 is separated from the payload 1, the stored parachute 2 is released.
By bundling the zenith part with a constant tension, the parachute can be released more reliably.

[0014]

As described above, according to the present invention, the posture of the payload of the flying body that discharges the parachute in the air after launch is stabilized and the parachute is damaged by providing a simple separating device for the parachute. It is possible to prevent the airborne time, lengthen the airborne time, prevent the electronic equipment in the payload from being damaged by the impact, and ensure the operation reliability.

[Brief description of drawings]

FIG. 1 is an explanatory diagram of a flying object according to an embodiment of the present invention.

FIG. 2 is an explanatory diagram of a flying object according to an embodiment of the present invention.

FIG. 3 is a diagram showing a flying vehicle sequence according to an embodiment of the present invention.

FIG. 4 is an explanatory view of a stable umbrella separating mechanism according to an embodiment of the present invention.

FIG. 5 is an example of a conventional flying object.

FIG. 6 is an explanatory diagram of a conventional flying object.

FIG. 7 is a diagram showing a conventional flying object sequence.

[Explanation of symbols]

 1 Payload 2 Parachute 3 Suspension line 4 Parachute unit 5 Propulsion device 6 Stabilizing wing 7 Stabilizing umbrella 8 Stabilizing umbrella separating device 9 Plate 10 C-ring 11 Slider 12 Actuator 13 Groove 14 Trigger pin 15 Conventional flying body 16 Surface ship 17 Guided flight body

 ─────────────────────────────────────────────────── ─── Continued front page (72) Inventor Akihiko Ono 325 Kamimachiya, Kamakura City Mitsubishi Electric Corporation Kamakura Factory (72) Inventor Hidetoshi Ibusuki 325 Kamimachiya Kamakura City Mitsubishi Electric Corporation Kamakura Factory (72) Inventor Ryujiro Kurosaki 325 Kamimachiya, Kamakura City Mitsubishi Electric Corporation Kamakura Factory

Claims (3)

[Claims] 1. In a flying body that is launched from the ground or onboard, emits a parachute after a certain period of time, and floats down using the parachute, a payload located in front of the flying body and a flying body immediately after the launch. A parachute that is stored inside and is connected to the payload via a suspension line, and similarly immediately after launch, it is stored inside a flying vehicle and is connected to a plate located behind the parachute via a suspension line. A flying body comprising a stable umbrella and a separating device for separating the stable umbrella after a predetermined time, deploying the stable umbrella first, and discharging the parachute after a predetermined time. 2. As the separating device, a C ring fitted into a groove provided in the plate, a slider inserted into a notch of the C ring to expand the C ring, and an actuator for moving the slider. A flying body characterized by having a groove into which the above-mentioned C ring extended is provided on the inner surface of the outer cylinder of the flying body. 3. The actuator operating means includes:
A flying object characterized in that it has a trigger pin in the actuator, and the actuator is triggered by pulling out the trigger pin by an aerodynamic load applied when a stable umbrella is deployed.