JPS58217200A - Propelling device for projectile - 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 [0011] A device that needs to be deployed at a location remote from the launch location;
The present invention relates to a projectile launcher for launching a device containing a projectile.

Multi-pole projectile launchers have been developed that use air or gas under pressure to propel the projectile from the launch pad. However, these have been found to have several drawbacks, particularly when used to launch devices containing projectiles.

In one type of launch pad previously proposed, the projectile is held in place within the launch chamber by a latching mechanism while air under pressure is applied to the base of the projectile 9. This projectile is
It is fired by releasing the latching mechanism and forcing compressed air to act on the base of the projectile to propel it along the barrel.

A disadvantage of this type of launch pad is that very high loads are generated by the compressed air acting on the base of the foam body before launch, so a very robust releasable latching mechanism is required. Furthermore, the projectile must be of such a design that the latching mechanism can cooperate with the projectile.

Nine other types of launch pads have been proposed so far.

Air under pressure is sealed from the launcher's fuselage by a fragile disc that ruptures to allow air to flow into the launcher's fuselage during launch. The disc may be designed to be destroyed by compressed air applied to it exceeding a predetermined pressure or by a pricking device. The major drawback of this launch pad is that the disc requires replacement after each launch.

- In yet another proposed launcher, air under pressure would be supplied to the launcher's body from a reservoir under the control of a valve remote from the body, and the firing of the projectile would be effected simply by opening the valve. It will be done. A disadvantage of this launch pad is that the valves used are slow to react and result in a loss of flow between the reservoir and the fuselage as well as subsequent loss of propulsion energy.

In further previously proposed launch pads, a chamber for admitting air under pressure communicates with the bore of the fuselage through one or more lateral openings in the fuselage, and these openings communicate with the interior of the fuselage when the projectile is ready for launch. When in position on the fuselage, it is sealed by the projectile itself. the projectile is launched by advancing the projectile to a position where the one or more lateral openings are no longer covered;
Pressurized air then flows from the chamber and acts on the projectile base to accelerate the projectile along the fuselage.

A disadvantage of this launch pad is that the projectile sidewall must be able to withstand the pressure of air applied to it through one or more lateral openings. Particularly for projectiles of considerable size, the walls of one or more fast-acting projectiles must be of strong construction and must be made of lightweight, low-strength materials. I can't. Moreover, calculations have shown that more energy can be used to accelerate this wall section of the projectile than is required to accelerate the useful payload.

It is known that a large amount of force is required to manually force the projectile into the launcher. For large launchers, this amounts to several thousand newtons, making loading extremely inconvenient.

A need sometimes arises for a launch pad that can be used as a trial device that is required to withstand high propulsion forces.

The proposed launch pad, in which the projectile itself isolates pressurized air from the launch pad's body, however, contains equipment that requires the projectile to be of small size and therefore durable and heavy. Therefore, the above objective is unsatisfactory.

A large dummy projectile can be used to separately achieve the necessary seal and force harvesting to be applied to the projectile containing the device along the fuselage. Quite heavy.

The object of the invention is to provide a projectile launcher for the full launch of a projectile under the action of air or gas under pressure, which device does not suffer from the drawbacks mentioned above. be.

According to the invention, the projectile to be propelled is arranged in use in a fuselage having an axial internal bore km, containing a fluid under pressure and through seven or more lateral openings in the fuselage. a chamber for communicating with the aperture, and a closing member movable between a closed position in which the opening or openings are closed and an open position in which the opening or openings are no longer closed. An enclosed propulsion device is provided for propelling a projectile under the action of a fluid under pressure.

Preferably, the closure member comprises a sleeve mounted coaxially with respect to the bore of the body and axially positionable along the body between a closed position and an open position.

In a preferred embodiment of the invention, sleeve displacement means are provided for generating an axial displacement load on the sleeve, which generates a predetermined initial displacement of the sleeve in the direction from the closed position to the open position; The sleeve is configured such that upon a predetermined initial displacement from the open position to the open position, the sleeve is subjected to an axial displacement load which accelerates the sleeve to the open position by fluid under pressure from the chamber and the body. The sleeve is further arranged in such a way that, when it is in the closed position, the sleeve is not subjected to axial displacement loads by fluid under pressure in the chamber or axial displacement loads which tend to maintain the sleeve in the closed direction. constructed and arranged to receive.

In an inventive embodiment described hereinafter, the fuselage is formed with an axially extending circumferential guide slot;
The confine sleeve is axially slidable within the guide slot between a closed position and an open position.

In a preferred embodiment, the circumferential guide slot is formed in a forwardly extending portion of the rear end of the fuselage and the sleeve is movable rearwardly from a closed position to an open position. The inner surface of the sleeve mates with the interior bore of the body, and the sleeve is arranged to abut and engage the interior bore of the body when in the closed position.

Means are provided for feeding the end face of the end of the sleeve projecting from the slot to create an axial displacement load on the sleeve to move the sleeve from the closed position to the open position.

In another embodiment of the invention to be described, the sleeve is mounted within the enlarged body and in the annular space provided by the chamber, and the guide slot is formed within the enlarged body.

One embodiment of the invention to be described hereinafter is that of the fuselage.

A projectile launcher for launching a projectile into the air from a fuselage with an open front end, and the projectile propulsion device according to the present invention has a front end of the fuselage closed to receive the impact force from the projectile/body. It can be used to generate a shock load by arranging it to be symmetrical.

Preferably, the fluid used is air or gas under high pressure.

Embodiments of the invention will now be described by way of example with reference to the accompanying drawings, in which: FIG.

Referring first to FIG. 1, the projectile shown in FIG. is held against the rear end surface of the intermediate surplus part/3 by a plurality of screws/l which are attached to the intermediate body part 13 by a plurality of screws shown in FIG. 1. /A and /7 are fixed.

End part /V: consists of a hollow cylindrical section /, 9 terminating in a flange 20, by means of which a flange extends into the vertical part /1l-1. It is fixed to the end face of the intermediate rope section /3.The fourth section 17 is likewise formed with a hollow cylindrical section, which is closed at the end section by the two end sections. A 7 flange λ3 is provided, by means of which the end part/7Vi is fixed to the end face of the intermediate body part/3.
- the cylindrical sections of the end parts /j and 77 are radially separated from each other and form an axially extending circumferential guide, a slotter, which is a sleeve that can be slid into the throttle; Receive 2 evenings.

The intermediate body 13 is formed with a cylindrical wall section and end sections 27 and 2t, which together with the cylindrical section of the end section /l form an annular space 2, which is shown in FIG. As shown in Sleeve 2! This space is closed from the inner hole of the fuselage by the sleeve 2! is shown in FIG. Ni sleeve 2 that communicates directly with the inner hole of the fuselage through the sleeve! engages with the seals 3/32 at the position shown in FIG. 1 and abuts against one rear end face of the forward part/2 of the fuselage. The O-ring seals 33 and 3 are provided in the end portions of the cylindrical areas 1 and 17, and the O-ring seals 3!゛ is guide slot 24! installed at the rear end of the

Furthermore, seals 3-3 are also provided.

Inlets ≠o, 4ci and ≠2 are internally threaded to receive high pressure hose fittings and provide compressed air for operation of the firing device. The inlet 4cO communicates directly with the annular space Kota, and air under pressure is supplied to this space to emit one shot! 3, the projectile is front-loaded to the fuselage /l and rests on a spacer screw 73 which is screwed into the section λ in the firing position. Human Log - is Dahekto/
4t2. /4tj and l≠Hiro through guide slot 2μ
Communicate with.

Air under pressure is supplied to slots 2μ~. Entrance 44/
In order to supply air under pressure to the μ sleeve, it communicates with the intermediate end surface of the sleeve and tube 2 through the duct l≠l.

The sleeve is then moved from the closed position toward the open position shown in FIG.

An air control system for controlling the application of air under pressure to the inlets Lθ to L is also shown in FIG. - Valve ≠ 3 and Hiro ≠, 0 release boat to the atmosphere is provided 2
It is equipped with a position on-off valve, a regulating valve with a cooperating stop valve, a pressure regulator with a discharge port to the atmosphere, and a pressure gauge.

Air under high pressure from a supply cylinder (not shown) is
Added to the input part of the control system ≠ 2, 4, 5,
5 through line 10 to the 2-stand valve≠Y, this valve is connected to line 10 and the output line in the position shown! Provide communication between /. The air under pressure in the line 1 is spring-biased to the cut-off position shown in Figure 3 at two positions fP≠3.
Air under pressure is added to the output line! 2. Air under pressure is likewise deflected from line j≠ to the cut-off position as shown in FIG. 3 by valve 4! ≠, air under pressure is supplied to the output line j
Prevent it from being supplied to j. Finally, air under pressure Vi to line si, line j6 and a manually operable regulating valve l.
is applied to output line j7 through the

In the position shown in FIG. 3, valve 4L3. By opening the regulating valve, air under pressure is supplied to the inlet 4cOVc of the device shown in Figs. 1 and 2, and the annular space 2
The primary valve 4L4 is used to start the 5-launch device, which uses highly pressurized air! is actuated and pressurized air from the line ≠ is passed through this valve from the position shown in FIG.
/l/ (supplied and also ducted) /Hiroshi/1 is supplied to the intermediate front end face of the sleeve 2j through the valve ≠ μ, and the 3 population ≠ 2 is shown in Fig. 3 by the valve 3. Valve IA3 shown in
Since it is connected to the atmosphere by standing upright, the sleeve 2jμ launch H
Sleeve 2 moved under high pressure air behind 1t
The pickpocket 2j is rapidly accelerated to the retracted position shown in FIG. Due to rapid retraction of sleeve 2j.

The base of the projectile j3, which is held apart from the end section by a cent screw 73, is acted upon over the entire area of the projectile base by 0770 pressure air from the chamber.

The projectile j3 is propelled along the forward part /2 of the fuselage with high acceleration and launched from the end of the fuselage. Projectile! After 30 shots, the pressurized air filling the four-way space 2 is expended and the device must then be reset to fire the next projectile.

Reset the launcher shown in Figures 1 and 2.

Control valve φ3 lines the air under pressure! from l to line jλ
And entrance 41! This is achieved by occasionally operating the a-control valve, like sending stones. The pressurized air at the inlet qλ is sent through the ducts /44u, /44J and /≠Hir to the rear end of the guide slot and forces the slide 2j. The regulating bowl 2 is then opened, pressurized air is supplied to the inlet bowl O through line j7 to refill the annular space, and this valve is then closed.

Do you want to prepare? A two-position on-off valve that is normally placed in the position shown in Figure J! In case of an emergency, it can be operated in the first place to release the line J/ to atmospheric pressure, and then release it from the air. ,−
t=5.8. . -6゜m'''25m's y,';゛: Intermediate parts 60 and 29. Removable breech, with a copper body closed by 62 and forming an end part 61. The middle raised part 60 has an outer cylinder/wall 63, a lower inner wall 6, and an upper inner wall 4j.
D-no*Mjilt! ,! : Co-Vc, Ml-like sky,
fjl 51:,, limited.

In addition, the intermediate portion 60 and the two-piece tail member t2 define a lateral opening 67 that provides communication between the annular space 6t and the inner hole of the body.
-144L7i defines a guide slot Arf for receiving and holding the sleeve 4M, and the sleeve is located in the slot 6♂ from the upright position shown in the figure. It can be slid in the retracted vertical position. Annular space A
Inlet lower θ is determined to supply the helmet pressure air, t;, p to fill A.
, 7/ and 7.2 are provided, and the pickpocket and -b 6 are μm.
The retracted lid 1 is moved from the position shown in Figure 1 and the sleeve 6 is reset for subsequent firing of the device. In order to cooperate with the 0-ring seal 1 sleeve t9, the inner wall is formed at 65 rLh. Also, a 4-part seal ri guide slot is provided to seal the rear end of the 4♂.

Launch l$! The operation of the device shown in Figure 3 is basically the same as the device shown in Figures 1 and 2, and is also shown in Figure 3. can be controlled by an air separate system such as
are replaced with input lowers 0, 7/ and 72 in Fig. ψ. However, projectiles! 31″i Remove the breech member t2 1
The breech can be loaded by inserting the firing book and replacing the breech member.

In the embodiment of the invention shown in FIG.
≠ is configured to provide an annular space 7j which communicates with the inner hole of the same body through the laterally open lower aperture, said opening is closed by a sleeve 77, which is connected to the open lower aro 4.
5, in which the sleeve is closed, can be slid into a non-retracted position in which the sleeve is retracted into the guide slot 7t- against the action of the biasing spring 7. The inlet tσ supplies pressurized air to the annular space 7! The inlet 1/ is provided to supply pressurized air to the periphery and edge 1r3 in the rear end of the sleeve 77. -' Sleeve 7
7, the sleeve is moved into an annular space 7 by the spring 7! is biased into the closed position shown in FIG.
- Another projectile! 3. The firing is achieved by lifting the rear end of the sleeve 77 from the base of the fuselage by separating the air under pressure into the inlet 1r/k, and the pressurized air in the annular space is released by the spring 7. This is effective in accelerating the sleeve 77 forward against the action of 7ff. Annular space 7
! Acting on the base of the book, it propels the book t''L forward along the book. The sleeve 77 is self-help reset to its closed position as shown in FIG. 5 by the action of the biasing spring 7. .The air control system as an embodiment of the invention is
Reset design valve ≠ 3 and omit population and entrance ≠ 0 and 4'
By replacing / with the inlet 10 and t/, the system shown in Figure 3 can be conveniently provided.

By controlling the acceleration and/or velocity of the sleeve in the embodiments of the invention described above, it is possible to influence the acceleration and velocity of the projectile. In accordance with the above-described embodiments of the invention, the two closure members are in the form of sleeves. However, the closure member may have other forms and alternative grooves, and it may also take the form of an end cap that closes the side opening in the same manner as the sleeve. Fukkotopoken Hail Lord 1

[Brief explanation of the drawing]

Figure 7 is a schematic longitudinal cross-sectional view of a projectile launcher according to an embodiment of the present invention in a ready-to-launch state. FIG. 2 is a schematic longitudinal sectional view of the device corresponding to that shown in FIG. 1 in a subsequent firing configuration. FIG. 3 is a schematic diagram of a pneumatic control circuit for controlling the operation of the apparatus shown in FIGS. 7' and λ. The second figure is a schematic vertical cross-sectional view of a projectile launcher according to the second (Q') embodiment of the present invention.
The figure is a schematic longitudinal sectional view of a projectile launcher according to a third embodiment of the invention.

Claims (1)

Claims: t. A fuselage having an axial bore in which the projectile to be propelled is disposed in use, containing a fluid under pressure and passing through one or more transverse openings in the fuselage. and a closing member movable between a closed position in which it closes the one or more openings and an open position in which it no longer closes the one or more openings. A projectile propulsion device for propelling a projectile under the action of a fluid under pressure. 2. The closure member is mounted coaxially with respect to the inner bore of the fuselage;
Claim 1, further comprising a sleeve displaceable along the body between a closed position and an open position in the c@ line direction.
! The device described by J.K. 3. The device of claim 2, wherein the sleeve is constructed and arranged so that when it is in the closed position, it is not subject to axial displacement by fluid under pressure within the chamber. Claim 1, wherein the μ sleeve is constructed and arranged such that when it is in the closed position, it is subjected to an axial displacement load which tends to maintain the sleeve in the closed position by a fluid under pressure within the chamber. The device described in. Claims 2 and 3 or ≠, which include sleeve displacement means for generating an axial displacement load on the sleeve, and generate a predetermined initial displacement of the sleeve in the direction from the closed position to the open position. A device according to any one of Item 7. & Based on a predetermined initial displacement from the closed position to the open position,
Claims Abstract: The foam sleeve is constructed such that the sleeve is subjected to an axial displacement load which causes fluid under pressure from a chamber to rise and accelerate the sleeve to an open position. ! Equipment described in Section. 2. The chamber is an annular space (around the body) extending circumferentially and formed as an enlarged nine body part, the annular space providing direct communication between said space and the inner bore of the body. 7. A device according to claim 7, wherein any of claims 2 to 6 communicates with the inner bore of the body through one or more openings. Ir, the body is formed with an axially extending circumferential guide slot, and the sleeve is capable of sliding axially within the guide slot between a closed position and an open position. Equipment described in Section. The device according to claim 1, wherein the circumferential guide slot is formed in a forwardly extending portion of the rear end of the fuselage, and the sleeve is movable rearwardly from a closed position to an open position. . 10. The device of claim 2, wherein the inner surface of the sleeve is adapted to fit within the bore of the body and the sleeve is arranged to abut and engage the bore of the body when in the closed position. /7. 11. The device of claim 10, wherein the sleeve is placed in a closed position to engage a circumferentially extending seal of the fuselage. 12. The sleeve displacement means comprises means for supplying fluid under pressure to the end face of the end of the sleeve projecting from the guide slot, creating an axial displacement load on the sleeve. , and equipment described in any one of Section 1.1. 13. The device according to claim 1, wherein the sleeve is mounted within the enlarged body and within the annular space provided by the chamber. 14. The device of claim 13, wherein the guide slot is formed in the enlarged barrel and the sleeve is movable forwardly from a closed position to an open position. 1. A device according to any one of claims 2 to 1, including biasing means for biasing the sleeve into the closed position. 14. The device of claim 13, wherein the biasing means comprises a spring. i7. A device according to any one of the preceding claims for the aerial launch of a projectile whose front end of the fuselage is open. Claim 1 for generating an impact load in which the forward end of the H fuselage is closed due to the impact force from the projectile.
The device according to any one of paragraphs 7 to 76.