JP3511087B2 - Flying object - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flying body that has a folding and deploying wing that is housed in a launch tube until it is launched and that is deployed with the ejection from the launch tube.

[0002]

2. Description of the Related Art A projectile launched from a launch tube is stored inside the launch tube until launch and is launched from the launch tube at launch.

FIG. 3 is a schematic view showing an example of a conventional flying object, and FIG. 3 (a) is an external view of the flying object seen from the side,
Figure 3 (b) is an external view of the aircraft as seen from the front.
The deploying wings are foldable and deployable, 1 is a flying body, 2 is a propulsion device, 3a is a wing fixed part, 3b is a wing rotating part,
Reference numeral 4 is a hinge portion, 5 is a shoe attached to the body of the flying body, and 6 is a deployment wing showing a state in which four blades are opposed to each other and folded. Here, the expanding blade 6 is composed of a blade fixing portion 3a, a blade rotating portion 3b, and a hinge portion 4 connecting them, and the hinge portion 4 is provided by the spring force of the hinge portion 4.
Has a force to open each of the wing expanding portions 3b outward. The deploying wings 6 of such a flying body 1 are
At the position where the outer circumference of the fuselage is divided into four equal parts when viewed from the machine axis direction,
They are attached to the rear of the propulsion device 2 (on the side opposite to the traveling direction of the flying body). Also, 7 is a hook, 8a
Is an umbilical connector on the flying side. Reference numeral 9 denotes a steering drive unit that supports the wing fixing unit 3a of the deploying wing 6 and drives it to a desired position to generate a desired rotational moment on the flying vehicle 1 after launch.

FIG. 4 is a view showing the projectile 1 in which the deploying wings 6 are folded and housed in the launch barrel 10. FIG. 4 (a) is a longitudinal sectional view, and FIG. 4 (b) is from AA. The cross-sectional view as seen, FIG. 4 (c) is a cross-sectional view as seen from BB, and 11 is a pair of supports for the flying body to slide inside the launch tube, 1
2 is a wing guide, 8 is a flying body 1 and a launch tube 10 before launching
Is an umbilical connector for electrically connecting the robot 1 to the flying body 1 side, and 8b to the launch tube 10 side. Reference numeral 13 denotes a restraint device disposed on the launch cylinder side at a position where it does not interfere with the deployment wing 6 of the flying vehicle 1. This restraint device 13 is attached to the rear end of the steering drive unit 9 and the propulsion device 2 Engaged with the hook 7 protruding to the outside of
The flying body 1 is restrained in the firing barrel 10 by a lock lever (not shown).

At the time of launching, the flying vehicle 1 glides by the thrust of the propulsion device 2 with the shoe 5 disposed inside the launch tube 10 and the support 11 in contact with each other. Similarly, the folded deployment wing 6 slides in the firing tube along the wing guide 12 while the wing deployment section 3 b is in contact with the wing guide 12 in the folded state. When the launch cylinder 10 is detached, the wing guide 12 and the wing rotating portion 3b are no longer in contact with each other, so that the folding of the deploying wing 6 is released in the direction shown by the arrow in FIG. 3 (b).
That is, the wing 3ba folded upward by the action of the unfolding spring (not shown) using the hinge portion 4 as a fulcrum is the arrow 2
When the wing 3bb is unfolded in the direction of 0 and the pressing force of the wing 3ba is subsequently released, the wing 3bb folded downward is indicated by the arrow 2
Expand as 1. Similarly, the opposite side to the machine axis is also deployed, and the wing deployment section 3b is fixed at the position indicated by the dotted line, and the flight is performed with a flying body having the original wing span. Generally, the folding of the deploying blades 6 and the blade guides 12 are arranged symmetrically so that the deploying order of the four deploying blades 6 is opened symmetrically with respect to the machine axis, and rolls generated when one blade is deployed I try to cancel each moment. When the flying vehicle 1 starts to move from a predetermined position inside the launch tube 10, the flying body side 8a and the launch tube side 8b of the umbilical connector 8 are separated from each other.

On the other hand, the restraint device 13 is fixed inside the launch tube, and when the projectile is stored in the launch tube 10, the hook 7 of the projectile 1 is locked by a lock lever (not shown). At the time of firing, by driving a lock lever (not shown) to open the hook 7, the flying vehicle 1 can slide in the firing tube 10 by a predetermined thrust of the propulsion device 2.

In the conventional flying body 1, the wings are folded so as to be efficiently housed in the launch tube 10 having a limited size. However, the support 11 and the wing guide 12 are provided on the inner surface of the launch tube 10.
Furthermore, it is necessary to attach the umbilical connector 8 and the restraint device 13. As shown in FIG.
In the same cross section, the support 11 had to be mounted at a position rotated 90 degrees around the machine axis with respect to the folded deploying blade 6 and the blade guide 12 in order to avoid interference. Further, there is a support 11 and a wing guide 12 in the longitudinal direction of the launch tube 10, and the position where the umbilical connector 8 and the restraint device 13 are attached is set to the rear of the deployment wing 6 so that the flying body can slide in the launch tube 10 at the time of launch. Is constrained to be placed in Furthermore, the propulsion device 2 for engaging the contact surface of the shoe 5 of the support 11
It was necessary to secure the processing accuracy of. For this reason, the maintainability of the flying object is deteriorated, and it is difficult to reduce the size of the launch barrel.

[0008]

As described above, the conventional flying body 1 launched from the launch barrel 10 has the following problems.

(1) When the support 11 is attached to the flying body 1 at a position facing the shoe 5 of the body, the support 11
And it is necessary to secure the processing accuracy of the body diameter to which the shoe 5 is attached so that the geometric deviation of the propulsion device 2 does not increase.
Fitting adjustment for attaching the support 11 is difficult.

(2) Since the support 11 in the launch tube 10 needs to be mounted at a position rotated 90 degrees around the machine axis with respect to the wing guide 12, a space for mounting other components such as the umbilical connector 8 and the restraint device 13. Is limited, and miniaturization is difficult.

(3) Since the umbilical connector 8 is attached to the rear portion of the flying body 1, it is necessary to provide the body with a bulge so that the wiring can be routed to a device arranged in front of the propulsion device 2, Since the air resistance increases, the aerodynamic characteristics deteriorate.

(4) In addition, the restraint device 13 is used to fly the flying body 1.
Since it is attached to the position facing the rear end of the
Since it is necessary to lengthen the launching cylinder 10 to the outside of the length, it is difficult to reduce the size.

The present invention has been made in order to solve the above problems, and minimizes the difference between the diameter of a flying fuselage having a deploying wing and the inner size of a launch tube that houses it. , The aim is to reduce the size of the launch tube and the size of the flying body and improve maintainability.

Other objects and novel features of the present invention will be clarified in the embodiments described later.

[0015]

In order to achieve the above object, a first invention of the present application is to provide a projectile housed in a launch tube before launch and ejected from the launch tube at the time of launch, provided at the rear part of the fuselage. a propulsion device that is, the firing barrel when stored being respectively folded <br/> folded to face each other pair of blade surface in the direction towards the shaft, expansion of the two pairs of deployed from the shaft after firing in the direction towards the outside A wing and a steering drive unit located behind the propulsion device, supporting the deploying wing and driving the deploying wing ;
In the machine axis direction so as to protrude from the body diameter of the propulsion device.
Along with a pair of hangers attached to the body
Eh, face the wing surfaces of the two folded deployment wings, respectively.
Attached to the inner surface of the launch tube, the longitudinal direction of which is the
A pair of guide rails arranged so as to coincide with the axial direction
On the other hand, the hanger is slidable and
The two pairs that have been folded and slid along the guide rails .
The deployment wing of the
A pair of wing guides attached to each row are brought into contact with each other and folded.
Holding the collapsed state, the folded length of the two pairs of expansion wings (d6) is characterized substantially that same or less than the cylinder diameter of the propulsion device.

The flying body according to the second invention is the flying body according to the first invention, wherein the folded body of the fuselage is used.
It is a position off the surface facing the two pairs of deploying wings,
One is provided in front of the propulsion device, and the launch tube is provided before launching.
Umbilical connector that is connected to and disconnected at launch
It is characterized by comprising a.

[0017] In addition, the flying object according to the third aspect of the present invention, the first
1st or 2nd invention WHEREIN: The said steering drive part is the said propulsion.
The outer diameter of the device is smaller than that of the device
The wing is installed between the outer periphery of the steering drive section and the inner surface of the launch tube.
Before being folded, the outer periphery of the steering drive is folded
A restraint device is provided at a position off the opposing surfaces of the two pairs of deploying wings.
Is placed and is restrained by the restraint device until it is launched.
It is characterized by the fact that it has been done.

[0018]

[0019]

[0020]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of a flying object according to the present invention will be described below with reference to the drawings.

1 and 2 show an embodiment of a flying body according to the present invention, and FIG. 1 (a) shows a flying body housed in a launch tube rearward (opposite to the traveling direction of the flying body). ), FIG. 1 (b) is a cross-sectional view of the projectile housed in the launch tube seen from the front, and FIG. 2 (a) is the longitudinal direction of the rear part of the projectile housed in the launch tube. 2 (b) is a sectional view of FIG. 2 (a) rotated by 90 degrees. In these figures, 30 is a steering drive unit of the flying vehicle 1, 31 is a hanger fixed to the body of the flying vehicle, 3
Reference numeral 2 denotes a guide rail fixed to the inside of the firing barrel 10, and other points are the same as those of the conventional example shown in FIGS. 3 and 4.

The deploying blades 6 of the flying vehicle 1 according to the present embodiment are located behind the propulsion device 2 and are attached to the steering driving unit 30 in two pairs. The (blade rotating part 3b) is folded so as to face each other. That is, the deploying wing 6 abuts on the pair of wing guides 12 attached to the inner surface of the launching barrel 10, and holds the folded state. Here, the steering drive unit 30
Has a diameter d30 smaller than the diameter (body diameter) d2 of the propulsion device 2, which is substantially equal to the diameter of the body of the flying vehicle 1. Further, the distance d6 between the two pairs of blades of the folded deploying blade 6 is determined by the distance between the pair of blade guides 12 arranged inside the launching cylinder 10, but here the diameter d2 of the propulsion device 2 is determined. It is folded smaller.

Therefore, since the distance d6 between the two pairs of blades of the folded deploying blade 6 is smaller than the diameter d2 of the propulsion device 2, a position protruding radially from the outer periphery of the propulsion device 2 having the diameter d2. A convex hanger 31 is provided (fixed to the fuselage of the flying body), and the wing guide 12 inside the launching cylinder 10 is attached to the same surface in the longitudinal direction.
It is possible to dispose a pair of guide rails 32 having a concave cross section that fits with the hanger 31 in parallel with the pair of wing guides 12 (fixed to the inner surface of the firing cylinder). The pair of guide rails 32 are arranged and fixed on the inner surface of the firing barrel 10 so that the longitudinal direction thereof coincides with the machine axis direction.

Here, a plurality of hangers 31 are arranged and fixed in the longitudinal direction on the surfaces facing the outside of the diameter d2 of the propulsion device 2, respectively, and in the state of being slidably fitted to the guide rails 32. The flying body 1 slides linearly in the launch tube 10 and ejects from the front of the launch tube 10. At this time, since the hanger 31 of the flying body 1 in the launch tube 10 is located outside the folded deployment wing 6, the deployment wing 6
The hanger 31 and the hanger 31 are on the same surface facing each other, but the firing cylinder 10
It does not interfere with the inner guide rail 32 and the blade guide 12.

Therefore, the guide rail 32 in the firing barrel 10
Since the wing guide 12 and the wing guide 12 can be mounted on the same surface, other components such as the umbilical connector 8 that is connected to the firing barrel 10 before firing and is disconnected when firing, or fly to before firing A space for mounting the restraint device 13 for restraining the body 1 can be secured. In addition, the distance d6 between the two pairs of wings of the deploying wing 6 is set to the propulsion device 2
By making the diameter smaller than the diameter d2, the firing barrel 10 can be downsized.

Further, since the pair of guide rails 32 which are linear and have a simple cross section are used, the hanger 31 is mounted on the propelling device 2.
The guide rails 32 are attached to the outer periphery of the firing rail 10 at positions facing each other, and are fitted into the guide rails 32 in a concave-convex shape. Here, as shown in FIG. 1 (a), in the flying object 1, the restraint of the position in the i direction is determined by the gap between the uneven fitting surface formed by the hanger 31 and the guide rail 32. It may be processed so that the 32 contacts. In addition, the j direction orthogonal to the i direction shown in FIG. 1A is as follows. As shown in the figure, the hanger 3
A gap s is formed between the fitting portion of 1 and the guide rail 32.
Here, the wing guide 12 is arranged inside the launching cylinder 10 in parallel with the guide rail 32, and suppresses the force of deploying around the hinge portion 4 of the deploying wing 6. That is, the restraint of the position in the j direction is performed by stably balancing the deploying force of the deploying vane 6 by the pair of vane guides 12, and at this time, substantially equal gaps s are formed on both sides of the propulsion device 2.

Therefore, since the position of the flying body 1 in the i direction and the j direction in the cross section orthogonal to the machine axis is restricted, the flying body 1 is stable when stored in the launch tube 10, and further, When the projectile 1 is ejected from the launch tube 10, the projectile 1 can slide stably in the axial direction. Further, since the support attached to the inner surface of the launch tube at the position opposite to the shoe of the fuselage of the flying body 1 is abolished, it is possible to secure the processing accuracy of the propulsion device 2 for engaging the contact surface of the shoe of the support. It became unnecessary. Further, since the hanger 31 and the guide rail 32 are used in place of the shoe and the support having a complicated shape, the position adjustment becomes easy and the maintainability is improved.

Further, as described above, since the guide rail 32 in the firing barrel 10 and the wing guide 12 can be mounted on the same plane, the guide rail 32 and the blade guide 12 can be mounted in the axial direction 9
The folded deploying blade 6 does not pass in the direction rotated by 0 degree, and the umbilical connector 8 can be provided in front of the propulsion device 2 in this space where the guide rail 32 and the blade guide 12 are not disposed. Becomes

Therefore, since the umbilical connector 8 can be attached in front of the propulsion device 2, the propulsion device 2
The swelling of the wiring leading to the device (not shown) disposed in front of the device is eliminated and the air resistance is not increased, so that the aerodynamic characteristics are not deteriorated.

Next, since the diameter d30 of the steering drive unit 30 is made smaller than the diameter d2 of the propulsion device 2, the steering drive unit 3 is a portion where the deploying blades 6 in the machine axis direction are not provided.
A space can be secured between 0 and the propulsion device 2. That is, the hook 7 provided at the rear end of the propulsion device 2 is inside the firing barrel 10 so as to engage with the hook 7, and the firing barrel 10 and the steering drive unit 30.
It is possible to provide a restraint device 13 between them.

Therefore, the restraint device 13 attached to the launch tube side is different from the hook 7 provided at the rear end of the propulsion device 2 in relation to the hook 7.
It can be provided in a space in the longitudinal direction outside the steering drive unit 30. Therefore, since the restraint device 13 can be housed within the length range of the flying body 1, the launch barrel 10 can be downsized.

The flying body 1 constructed as described above is
Since the distance d6 between the two pairs of folded deployment wings 6 is smaller than the diameter d2 of the propulsion device 2, the cross-sectional area of the firing barrel 10 can be reduced. Further, since the guide rail 32 and the wing guide 12 are on the same surface facing each other in the cross section of the firing cylinder, the umbilical connector 8 and the restraint device 13 are provided on the remaining facing surfaces.
Can be provided.

In the above embodiment, the case where the two pairs of distances d6 of the folded deployment blades 6 are smaller than the diameter d2 of the propulsion device 2 is illustrated, but the two pairs of distances d6 of the folded deployment blades 6 are illustrated. And the diameter d2 of the propulsion device 2 may be substantially the same, and in this case, substantially the same effect can be obtained.

In the above embodiment, the umbilical connector 8 and the restraint device 13 are provided on one side of the line connecting the pair of guide rails 32 in the cross section (FIG. 1) of the firing barrel 10. However (see FIG. 2), it goes without saying that the umbilical connector 8 and the restraint device 13 may be arranged at positions on both sides facing the line connecting the guide rails 32.

Although the embodiment of the present invention has been described above, it is obvious to those skilled in the art that the present invention is not limited to this and various modifications and changes can be made within the scope of the claims. Ah

[0036]

EFFECTS OF THE INVENTION Since the present invention is constructed as described above, it is possible to obtain a small-sized and well-maintained projectile, and also to downsize the launch tube for storing the projectile. Further, the following effects are achieved.

(1) Since the hanger and the guide rail system are used, the maintainability is improved, and the guide rail and the wing guide are opposed to each other on the inner side of the firing cylinder and the deploying wing.
Since they are arranged parallel to each other, it is possible for the flying object to glide stably.

(2) A space for mounting components such as an umbilical connector and a restraint device can be secured,
The launch cylinder can be downsized.

(3) The outer surface of the flying body does not have a bulge due to wiring, and aerodynamic characteristics are not deteriorated due to an increase in aerodynamic resistance.

[Brief description of drawings]

FIG. 1 is a cross-sectional view showing an embodiment of a flying object according to the present invention as viewed from the rear and the front in the radial direction.

FIG. 2 is a cross-sectional view of an embodiment of a flying object according to the present invention, in which cross sections in the machine axis direction are viewed at 90 ° intervals.

FIG. 3 is a schematic external view of an example of a conventional flying body viewed from the side and the front.

FIG. 4 is a cross-sectional view in an axial direction and a radial direction in which an example of a conventional flying object is housed in a launch tube.

[Explanation of symbols]

1 flying body 2 propulsion device 6 deployment wings 7 hooks 8 Umbilical connector 10 launcher 12 Wing guide 13 Restraint device 30 Steering drive 31 Hanger 32 Guide rail

─────────────────────────────────────────────────── ─── Continuation of the front page (56) References JP-A-2-13795 (JP, A) JP-A-9-101098 (JP, A) Fukuihei 2-14595 (JP, U) (58) Field (Int.Cl. ⁷ , DB name) F42B 10/14 F41F 3/04

Claims (3)

(57) [Claims] 1. A projectile, which is housed in a launch tube before launch and is ejected from the launch tube during launch, with a propulsion device provided at the rear of the fuselage, and a pair of wings in a direction toward the axle when the launch tube is stowed. Face
Each folded to face each other, and development blade two pairs deploying from the shaft after firing in a direction toward the outside, the propulsion device situated in the rear, the Expand blade to the support and steering drive for driving the expansion wings Part, and in the machine axis direction so as to protrude from the body diameter of the propulsion device.
Along with a pair of hangers attached to the body
For example, prior to each face the blade surface of the expansion blades of the two pairs of folded
It is attached to the inner surface of the launching cylinder and the longitudinal direction is the axial direction.
Pair a pair of guide rails that are
The hanger is slidable, and the hanger is
The two pairs of deploying wings that slide along the idrail and are folded are attached to the inner surface of the launch tube.
A pair of wing guides mounted parallel to the guide rails.
Holding the state of being folded respectively in contact with the de, Fei said folded length of said two pairs of expansion wings (d6) is characterized in that less substantially equal to or than the cylinder diameter of the propulsion device Shobo. 2. The two pairs folded in the body
And a umbilical connector that is provided in front of the propulsion device and is connected to the launch tube before launching and is disconnected from the surface facing the deploying wing of the umbilical connector. The flying object according to claim 1 . 3. The steering drive unit is outside the propulsion device.
Size is small, development blades of the two pairs of folded is provided between the outer periphery and the launcher inner surface of the steering drive unit, the
A restraint device is disposed at a position outside the facing surfaces of the two folded deployment wings on the outer periphery of the steering drive unit ,
The flight vehicle according to claim 1 or 2 , wherein the flight vehicle is restrained by the restraint device before being launched .