JPS60101499A - Projectile propulsion device - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention is directed to the axial direction Vc of the projectile 7 launch tube. The present invention relates to a VC for 6-stroke propulsion that utilizes pressurized fluid to do so.

In conventional projectile launchers, a chamber containing pressurized gas is communicated with an inner bore of the launcher through one or more lateral holes in the launcher, and the chamber is in communication with an inner bore of the launcher when the launcher is ready for firing. The projectile itself is configured to close the side hole of the launch tube. To launch the projectile, the projectile is first advanced to the position where the side hole is opened, and this causes pressurized gas to flow from all chambers into the inner hole of the launch tube and the proximal end of the projectile. is applied to accelerate the projectile along the launch tube, and one projectile is fired from the front end of the launch tube.

In other conventional projectile launchers, seven or more lateral holes in a single tube are sealed by a sleeve coaxially attached to the inner hole of the tube. This sleeve is displaceable in the axial direction along the launch tube between a closed position where the side hole is sealed and an open position where the side hole is opened. It is configured to flow in and act on the proximal end of one projectile.

The conventional projectile launchers mentioned above are used for arranging a line at a point R, e.g. For this purpose, all equipment is placed inside one projectile, all the projectiles are fired, and when the projectile reaches a remote point, equipment is removed from one projectile or removed from the projectile. Equipment will be automatically released upon use for such purposes.

It has been established that the directional stability of a projectile during flight is adequate, and no measures have been considered to improve the directional stability by rotating a single projectile, or alternatively,
It was considered unnecessary.

However, it has been determined that improved directional stability of a projectile is particularly desirable for some applications. By forming a full rifling in the inner bore of the launcher, or by
Previously known methods of inducing rotation by providing inclined fins on the projectile increase the complexity of the projectile or projectile structure.

This is considered inappropriate because it increases manufacturing costs.

An object of the present invention is to provide a projectile launcher with a simple structure that induces rotation in one projectile.

According to the invention, there is provided a launch tube with an axial hole in which the projectile to be propelled is located in use, and a feed hole in this launch tube? a pressurized fluid supply device for supplying pressurized fluid to the inner bore of the projectile through the feed tube, so that when actuated, pressurized fluid flows from the supply device through the supply hole to the proximal end of the projectile. In a projectile propulsion device that propels a projectile by the action of a pressurized mL body configured to act to accelerate the entire projectile within the launch tube to a predetermined axial velocity, pressurized fluid from a supply device is supplied to the supply hole. or through another feed hole into the inner bore of the launch tube tangentially or partially tangentially to the proximal end of the projectile and configured to rotate the projectile at a predetermined rotational speed. It is characterized by being

Preferably, the pressurized fluid fed into the inner bore of the launch tube through the feed bore is tangential or partially tangential to the inner bore of the launch tube to accelerate the projectile to a predetermined axial velocity. The projectile is also configured to rotate at a predetermined rotational speed when directed into the inner bore of the launch tube.

In the embodiments of the invention described below, a deflection element is provided in the feed bore which directs the pressurized fluid tangentially or partially tangentially with respect to the inner bore of the firing tube. At least seven feed holes or feed holes may extend around the entire circumference of the entire launcher, and deflecting elements may be provided within the overall feedhole at equidistantly spaced locations around the launcher.

In the embodiment of the present invention to be described later, each deflecting element is constituted by a deflecting plate and is provided on the line of intersection of the lever in a plane inclined with respect to the radius of the inner hole of one firing tube and the inner hole of the firing tube.

Sara K again. As required.

Each deflector plate f: may be positioned in a plane parallel to the l1III+ line of the inner hole of the launching oil, thereby creating a spiral flow of the pressurized fluid along the inner hole of the launching fluid W; can.

In the embodiments of the invention described below, each baffle plate is provided in a fixed position within the feed hole. Alternatively, each baffle plate may be angularly adjustable within the feed hole. Furthermore, each baffle plate may be configured to be fully angularly adjustable about a pivot axis extending parallel to the axis of the launch tube to vary the rotational moment applied to the projectile.

In an embodiment of the present invention to be described later, a pressurized fluid supply device is provided with a chamber for containing pressurized fluid, and this chamber is communicated with an inner hole of the firing cylinder through a supply hole. Be smart.

The chamber is formed by an annular space extending around the launch tube.

This allows direct communication between the annular space and the inner hole of the firing tube. a valve device is provided to control the supply of pressurized fluid from the chamber to the inner side of the launch tube through the supply hole;
Preferably, the valve device is formed by a sleeve coaxially attached to the inner hole of the firing tube, and the sleeve is fully movable between a closed position where the supply hole is closed and an open position where the supply hole is fully opened. shall be. In another embodiment, the supply of pressurized fluid from the chamber through the supply hole to the inner bore of the launch tube is controlled by a projectile propelled by the device.

When firing the device, one projectile moves from the firing position in the inner bore of the launcher cylinder, where the supply hole is closed, to the forward position (where the supply hole is opened).
& can be moved.

In embodiments of the invention described below, the outer surface of the projectile is fully formed with rotation-inducing grooves, such that rotation at a predetermined rotational speed is caused by the action of pressurized fluid directed at the grooved surface. .

Hereinafter, embodiments of the present invention will be explained with reference to all the drawings.

As shown in FIG.
/, the rear end of this launch tube front part 7.20 is attached to the intermediate part 13 by a collar 74L, and the collar llI is attached to the first
Multiple screws/! Only one shown in the figure! by middle part 13
The two end portions 16 and 17 are held against the rear end surface of the intermediate Hi 3 by a plurality of screws 1g, only one of which is shown in FIG.

The hollow cylindrical part constituting the end part 16 has a flange 20 at one end, by which it is attached to the end face of the intermediate part 3. The end /7 likewise consists of a hollow cylindrical part 21, which
is closed at its front end by an end section 22 and is provided at its rear end with a flange 23 by which the hollow cylindrical section 2/ is attached to the end face of the intermediate section 13.

The cylindrical portions /l and /7 of the ends /l and -7 are radially spaced apart from each other by 11! l] A circumferential guide groove hole is formed extending in the linear direction, and a groove is formed in this groove hole 2≠.
J-Fλ! is attached so that it can slide freely.

The intermediate part 13 has a cylindrical wall section t and a tin section core, λ
The cylindrical portion l of the end 16 is woven into these portions.
An annular space λ is formed by the sleeve, and this annular space is opened by the sleeve co S from the inner hole of the launch tube.
Although the sleeve 2 is blocked as shown in the figure,
When j is moved to the position shown in Figure 1, the ju-shaped space λ opens directly into the inner bore of the launch tube through the bore 30f. The hole 30 is provided between the rear end wall of the front end portion 27 of the intermediate portion 811/j and the front end of the hollow cylindrical portion l, and a plurality of baffle plates io are provided in the hole 30 as shown in FIG. are arranged at regular intervals around the inner bore of the launch tube, these deflectors being partially oblique in the tangential direction VCfrj4 with respect to the proximal end VC of the launch tube, Sleeve 2! In Figure 1, place 71 female position 1st shift rC,
It engages with the seal 3/workpiece 32 and abuts against the rear end surface of the front part/2 of the launch tube. A cylindrical portion /F, -〇Ktd ring seal 33.3 is provided at the ends /1 and /7, and another ring seal j j is provided at the rear end of the guide a# hole λμ.
'i) i' provided. Also, other stickers 3z~
Three bars are also provided.

A projectile used in a launcher! 3 is the front 9 in the launch tube ll
1Il and is located on the end portion 22 of the end 17 of the firing tube in the firing position. Projectile! The cylindrical outer surface VC of the casing of No. 3 is provided with rotation-inducing grooves 73, and the projectile is activated by the action of the gas directed through the holes 30 and the grooves 73. 3 is rotated.

Person CJ≠0,4t/,≠2 is internally threaded to receive a high pressure hose fitting for supplying pressurized gas for actuating the launcher. Projectile! The inlet 〇 is in direct communication with the annular space λ which is to be supplied with all the pressurized gas that applies the thrust for launch.

Inlet ≠ 2 is a slot, 2 ≠ is a duct for supplying pressurized gas)
／≠! , /113, /+≠ and communicates with the guide groove hole 2μ. entrance! / is s IJ- via duct l≠/
It communicates with the intermediate end face of i2z and sleeve 2! The pressurized gas is fully applied to the sleeve to displace it from the closed position to the open position shown in FIG.

A control circuit for fully controlling the supply of pressurized gas to the inlet≠O-≠2 is shown in Figure 10, and this circuit includes an IJ to the atmosphere.
λ position spring-loaded control valves with respective IJ-ports≠3,1 fili1. IJ to the atmosphere - On-off valve with a float ≠ j, flow valve with check valve ≠ B, IJ to the atmosphere 14 - Pressure regulating valve with a float ≠
7 and a pressure gauge ur are provided.

High-pressure gas is supplied from the supply cylinder (not shown) to the inlet of the control circuit≠2, and is supplied to the second set of on-off valves≠j via the pipe jO, and this on-off valve is not shown. Conduit in the position of! 0 is connected to the output pipe jl. Conduit! The pressurized gas in 1 is supplied to the 2-position spring load control valve ≠ 3, which is held by a spring force in the shutoff position shown in Figure 3 and pressurized gas is supplied to the output line tacho. It prevents Similarly, the pressurized gas is supplied to the valve t≠ by the line j≠, and this valve is similarly held in the cutoff position by the spring force as shown in FIG. 3, so that the pressurized gas is supplied to the output line j! This prevents it from being supplied to Finally, the conduit! The pressurized gas in / is connected to pipe jt and manual flow valve 113f.
It is then supplied to the output pipe j7.

When the valve 4L3.4Lμ, ≠5 is in the position VC shown in Fig. 5, and the flow rate valve ≠B is open, the pressurized gas is
3 The inlet of the device shown in Figure 4 is supplied with annular space 2
Introduce high pressure gas into z. Next, the flow valve t is closed. To fire the firing device, the valve ≠ is then opened and moved from the position shown in Figure 3 to another position, and in this position the conduit! The pressurized gas in ≠ is supplied to the inlet ≠/,
Also, 91M in front of the middle of sleeve 4j via duct l≠/i
Acts on the surface. Since the inlet 4+-λ is communicated with the atmosphere by the valve ≠3 at the position of the valve≠3 shown in Figure 3,
The sleeve 2 is moved rearward into the firing device by high pressure gas. As the sleeve 2j moves past the seals 3/, 32 into the annular space 2z, the annular space -
The high-pressure gas in the sleeve 22 is removed from the sleeve.

Accelerate to the retreat position KA freeze shown in . Due to the rapid retraction of the sleeve λj, the pressurized gas is diverted from the baffle plate l0VC.
Therefore, it is directed toward the rear end of the projectile j3 in the tangential direction at 66 minutes, and acts on the rotation induction Tokai 73, thereby causing the projectile to rotate completely. At the same time, the pressurized gas acts on the proximal end of projectile j3 and propels the projectile along the forward part/2 of the launcher at a high velocity in the alI direction, bringing the projectile to the predetermined axial velocity and Fire from the tip of the launch tube at the planned rotational speed. After launching the projectile, the pressurized gas in the annular space Ko2 is consumed,
Therefore, it is necessary to reset the device to fire the next projectile. ``To reset the firing device shown in Figures 1 and 2, first, control valve 113'f is momentarily activated to supply pressurized gas to the line! 1 to pipe j2 and the inlet ≠. The pressurized gas enters the duct at the inlet port λ.

l≠3. /≠≠ to the rear end of the guide slot, thereby returning the sleeve 25 from the position 70 shown in FIG. 2 to the position shown in FIG. Next, open the flow valve≠6 and supply pressurized gas to the inlet≠O through the pipe j7f to fill the annular space 27 with pressurized gas again, and after filling, close the flow valve≠2. , the launcher is fully prepared to fire another projectile loaded from the front into the front of the launch tube. The two-position on-off valve ≠j, which is normally located in the position shown in FIG. ! 1 - Pressurized gas can be vented from the launcher by venting to the atmosphere.

Although not shown in the drawings, another embodiment of the present invention is a projectile! By sealing the bore 301,1 by itself, the sleeve can be omitted.In such a construction, the projectile 3 is mounted in the firing position, in which the bore 30 is closed. is completely sealed, and at the time of firing, the projectile is advanced along the launch tube // to open the hole 30f, which allows the pressurized gas in the nitrogen gap and 2z to flow through the hole 30 and close the rear end of the projectile. the projectile to the front of the launch tube ()
It is possible to generate the rotational and axial velocity required for firing from the target.

The pressurized gas flowing from the space λ through the bore 30f accomplishes the dual purpose of imparting rotational motion to the projectile and accelerating the projectile to the required axial velocity during firing. However, in some applications, pressurized gas from the space 277 may flow through seven or more holes into a first passage into the inner bore of the launch tube to cause the projectile to rotate. , the projectile along the inner bore of the launch tube acting on the proximal end of the projectile by flowing in a separate passageway through one or more other bores? Advantageously, it is configured to accelerate.

In implementation $11 of the invention described above with reference to the drawings, the baffle plate 10 is a fixed plate. However, in some applications of the device, the rotation applied to the projectile is such that the deflector is attached around the periphery of a pivot shaft running parallel to the axis of the launch tube and the angle of attachment is adjustable: It is desirable that the configuration be such that the power can be increased to kW.

Furthermore, for some applications of the device, the deflector plate IO is located in a plane oblique to the axis of the entire launcher and extends along the inner launcher bore in the direction of the opening r1.1 of the launcher. It is advantageous to provide a gas spiral 61e'.

In the embodiments of the invention described above with reference to the drawings, the device is preferably fired by pressurized air.

However, other gases such as nitrogen gas can be used as well.

In the embodiment of the invention described above with reference to the drawings, the annular space 2 forms a chamber for containing pressurized gas.

In another embodiment of the present invention, a chamber tray may be provided to contain a large system that is ignited to generate high pressure gas during full firing of the device f. In this case, the sleeve 2j is omitted.

In the embodiments of the invention described above with reference to the drawings, a projectile! 3 is ready for firing within the launch tube 1.2, in which the rear end of the projectile extends rearwardly completely across the bore 30. However, depending on the application of the launcher, it may be desirable to configure the projectile's trailing end in the firing position to extend rearwardly across only a portion of the bore 30.

[Brief explanation of drawings]

FIG. 1 shows a projectile launcher according to a first embodiment of the present invention in a ready-to-launch state, and FIG.
A diagrammatic longitudinal cross-sectional view showing the launch device shown in the figure in the next firing preparation state; Part 3 1 is a diagrammatic cross-sectional view of the device of FIG. The Figure is a control circuit diagram for controlling the operation of the apparatus shown in Figures 11.2 and 3. //... Launch 1','l), /, 2... Front of launcher, /3... Middle of launcher, /≠...Color, /4
, / '7... End part, /P... Hollow cylindrical part 1.20... Flange %, 2/... Hollow cylindrical part, -2, 2... End part 1.2 J Mountain flange, 2≠
...Circumferential guide slot 1.2J-...Sleeve, 2
6...Cylindrical wall portion 1.27. ．． 2g...Q:fi
ite minute, λri... annular space, 30... hole, J3
... Projectile, 73... Rotation-inducing groove. Engraving of drawings (no change in content) Procedural amendment (method) November 29, 1980 Dear Commissioner of the Patent Office 1, Indication of the case 1982 Patent Application No. 218762 2, Title of invention Projectile Propulsion Device 3. Relationship with the case of the person making the amendment Name of the patent applicant: S. Equipmant Limited 4, Agent

Claims (1)

[Scope of Claims] / A launch f11) in which the projectile to be propelled passes through an axial hole located inside the firing tube, and into this launch tube via a feed hole into the inner hole of the launch tube). JI+ Pressurized fluid supply device for supplying pressurized fluid? At the same time, when the ejector is activated, pressurized fluid from the supply device flows through the supply hole and acts on the nozzle and V ends of the projectile, causing the projectile in the launch tube to move toward the intended radial direction. A projectile propulsion system that uses the action of pressurized fluid to propel the projectile + mt
In, supply? (15 degrees of all pressure fluid passes through the supply hole and also through the other supply hole to the proximal end of the projectile - in the J-line direction or officially -) of the launcher in the line direction. The projectile propulsion device K+ is directed into the inner hole and rotates the projectile at a predetermined rotational speed change (1). Linear direction 1
710 pressure fluid is supplied into the inner hole of the launcher via the supply hole so as to be connected to the inner hole of the launcher. 794. The apparatus of claim 794, characterized in that the apparatus is configured to direct the projectile into the inner bore of the launch tube and rotate the projectile at a predetermined rotational speed.3. A device according to claim 2, characterized in that a deflecting element is provided in the feed hole for directing the feed hole in the cutting line direction or partially in the cutting line direction. 111. At least seven of the feed holes or feed holes extend around the entire circumference of the launcher, and deflection elements are provided within the feed holes at equal distances apart from each other along the length of the launcher. 5. The device according to claim 3, characterized in that each deflecting element is constituted by a deflecting plate, and
1] The hole is provided in a plane that is inclined with respect to the radius of the hole and at the line of intersection between this plane and the inner hole of the launch tube. 6. The device according to claim 5, characterized in that each deflector plate is located in a position j7 parallel to the axis of the inner bore of the launch tube. The device i3 described. 7. Each baffle plate has 111i4 holes inside the projectile.
I is located in a plane inclined to the line and from this V produces a spiral bit of pressurized fluid along the inner bore of the launch tube.
The special feature is that it has been successfully constructed to reduce 1L. '
The device according to item 5 of the scope of FW closing. r, each baffle plate is housed in the supply hole in a fixed position; ν;1r1゜? , each part b
8. Apparatus according to any one of claims 5 to 7, characterized in that the barrier is mounted in the supply hole so as to be adjustable in all directions. 10 Each baffle plate is the axis of the launch tube l1iVC mower1. A configuration in which the ileal moment that is applied to the projectile body by the 8-point rotation of the Kakuho around the pivot axis that extends parallel to the body is transformed into a structure (a special feature characterized by -/here). The apparatus according to claim 1.
11. Device pj according to any one of claims / to io, characterized in that it communicates with the hole. /2. The chamber is formed by an annular space extending around the launcher and communicates with the inner hole of the launcher via the feed hole, and the annular space formed in the chamber is in direct communication with the inner hole of the launcher.
The device according to claim 1/h, characterized in that: /3. Said supply hole? Claim 1/Claim 1 is characterized in that it also has a valve device that completely controls the supply of pressurized fluid supplied from the forward UC chamber to the inner hole of the launch tube through the tube. ! f″i
The apparatus according to item 12, the closing position where the valve device closes the supply hole and the supply hole? Claim 13, characterized in that a closing element is provided that is movable between an opening position and an opening position. 7. The apparatus of claim 7V-, further comprising a sleeve mounted coaxially with respect to the bore and displaceable axially along the firing tube between closed and open positions. /6. Control 1 to -9. by controlling the supply of 111 royal fluid supplied from the chamber to the inner hole of the launch tube via the fill feed hole to the projectile propelled by the device. 1 out of every 6 shots, 131 projectiles were fired 1)
The firing position in the ILlij hole in 2J, before opening the power supply hole; /, the device according to item 2. /7. Mij Rhyme 11 [I E fluid supply device is provided with gunpowder which generates cylinder pressure gas 5c, and this gunpowder is ignited when the device is fired. VCgt il+'
dressed as j. 1111 outside of the propelled projectile, 1111 rotational line grooves are formed, and external application of pressurized fluid directed to this grooved surface vCf-1131 rolling ball expansion of pre-rectangular shape 1 in
The device according to any one of claims 7 to 77, characterized in that it is configured so that g1 rotation occurs.