JPS62159000A - Expansible speed reducer - 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 When the gear reducer and the body suspended therefrom are launched from an aircraft or missile at high velocity, deployment of the gear reducer creates a severe shock due to the rapid deceleration.

Such shocks are often sufficient to cause structural failure of the reduction gear or damage to the payload to which it is attached. Prior art deceleration systems use parachutes, metal fin stabilizers, and ballet technology to decelerate small bombs in stages and reduce the incidence of damage. A common problem with such devices is that the speed up and down during dispersion often overstresses the speed reducer and causes it to fail.

For example, a parachute may lumber along at speeds of less than 1500 feet per second, but when it suddenly opens at high speed, the lines become tangled, disorienting, or break. Parachutes are also not suitable for use in forest areas, since they will get caught on branches and shrubs, thus preventing the load from hitting the target.

Metal fin stabilizers provide acceptable deceleration when loosening speeds are below 1600 feet per second, but at higher speeds they often fail structurally and can cause wobbling and instability when wide scattering is desired. resulting in trajectories and poor dispersion patterns.

U.S. Patent No. 4, issued to the same inventor.
The parasitic tote and balloon combination, referred to as the Balute technology, as taught in US Patent No. 215,836, offers numerous advantages over the prior art. In this case, the present invention provides further and significant improvements over the concepts covered in the patent.

SUMMARY OF THE INVENTION The present invention successfully disperses at speeds of 2600 C-1-2 or higher by providing air suction that maintains proper inflation and structural integrity of the device. It is related to varicoat technology that makes it possible to Following deceleration, the deceleration device continues to function as a bullet guidance and stabilization device C'j.

It is therefore an object of the present invention to provide a new high traction stabilizer that can be attached to ammunition so that improved reliability of operation is achieved.

Yet another object of this invention is to provide a high traction stabilizer that stabilizes when attached to a munition and decelerated to a preselected terminal velocity.

These and other objects and many of the attendant advantages of the present invention will be better understood from the following detailed description taken in conjunction with the accompanying drawings.

DETAILED DESCRIPTION OF THE EMBODIMENTS Referring to the drawings, the reference numeral 10 in FIG. A shaft 16 tightly secures the damper, which consists of an inflatable hollow flexible chamber 14, as described in U.S. Pat. No. 4,215,836.
may function in any convenient manner as suggested for the nut 28 and load mandrel 30 disclosed in .

Secondary ammunition or bomblet 12 includes an external, substantially cylindrical housing 18 with chambers 14 secured to one end thereof and sequentially spaced apart as indicated by spaces 24 and 26. A series of rectangular protrusions 20
and terminating in a lower edge 19 having 22. small bomb 1
The housing 18 of 2 contains all the essential elements necessary for a combat weapon of this type, including the explosive charge, the impact detonator and other sensor mechanisms adapted to feed and drive the explosive charge.
components (not shown). In addition, the housing 18 is in a state in which the chamber 14 is collapsed, i.e.
a somewhat conically shaped and concentric internal cavity or hollow storage space 3, volumetrically shaped to match the size and shape of the chamber 14;
including an inner wall 28 forming a 0. This allows for the sequential stowage of a number of small bomb assemblies around the longitudinal axis to occupy and cover the elongated cylindrical rocket payload section in a manner indicated by J- in FIG. can.

Referring to FIG. 2, the reducer 14 illustratively has a shape generally resembling an essentially flat star with three radially outwardly projecting lobes or wings 32. It is shown. The essentially star-shaped chamber 14 is
For example, a continuous seam, as suggested by a seam 138 coextensive with the outer terminal edges of both the flat top panel 34 and the slightly rounded bottom panel 36, may Panel 3 around each periphery of
4 to panel 36. Panel 36 contains sufficient material to form a slightly conical shape when chamber 14 is fully inflated as suggested by FIG. flat or flat, panel 3
6 gives a deeper thickness in the center of the chamber than at the outer ends of the rope 32. Each of the rows 132 has a long inflatable converting member that contacts the axially central portion of the chamber 14.・It is. 0-
The cut area between 132 and 132 is important for the performance of the reducer, as discussed below.

Attachment of the chamber 14 to the bomblet 12 is accomplished by using a plate 40 with small clinch nuts 42 secured to the inside of the lower panel 36, while the spacer ring 44 is secured to the outside of the panel 36. Plate 40 and spacer ring 44 are also secured together by a plurality of rivets, such as four equally spaced rivets of the type suggested by rivets h 46.

each one as schematically shown by hole 50 in FIG.
The addition of at least one hole proximate the outer end edge of 1-132 is in this case critical to the concept of the invention. It is through these three holes that the air flow necessary for expansion of chamber 14 is created. Since the firing rate of the assembly 10 is based on the operating characteristics of the bomb or missile being launched, the airflow rate into the chamber 14 can be adjusted by the size of the lobe holes 50.

The use of a drain or hood over each hole 50, such as drains 52 and 54 seen in FIGS. 1 and 2, is also of particular and great importance, as is the star-shaped shape of the chamber 14. ζ) hoods or pockets each form an upright cover located at, but spaced from, each of the holes 50 to direct a small portion of the external airflow around the chamber 14. A hole 5 which is captured or captured, a small portion of which is trapped and occluded, or otherwise covered by a pocket.
Inhale such a small portion into Bokeh 1 so that it is directed in the 0 direction. Thus, each pocket, indicated by pocket 52 in FIG. 2, has an open end portion 56, a blind open end portion 58, and side portions 60 and 52 extending therebetween. These portions include surfaces that slope from an air inlet area 56 open at one end toward a blind end 58 .
There is no exit or any escape from 8, so that the airflow entering inlet 56 is forced in the direction of hole 50 and into chamber 14.

Such a suction effect achieved, for example, by pockets 52 and 54 is particularly significant in this case for ensuring reliable and effective operation of the speed reducer. As can be seen from FIGS. 3 and 4, the sub-munition assembly 10, prior to deployment for combat use, is equipped with a reducer 14 in order to form a dense mass in the smallest possible space. are stored and loaded tightly folded and folded. This causes the highly compressed and compact mass of the chamber 14 to fit into a tight and intimate nested relationship within the concentrically formed cavity 30 at the center of each bomblet 12. You can get absorbed in it. However, when the secondary munition 10 is ejected into space while moving at high velocities of 2600 feet per second or more, the positive and violent effects occur because the compact mass of the collapsed chamber 14 is relatively stiff. This is necessary to ensure that it does not remain stuck like a ball, but is inflated and expanded by internal pressure so that the deceleration and stabilization function of the bomblet 12 occurs.

The forceful positive action described for unfolding the chamber 14 and inflating the chamber 14 is accomplished by the drains including items 52 and 54 described above. Thus, when collapsed, the chamber 14 is folded in such a manner that one or more drains or pockets, such as items 52 and 54, are exposed on the exterior surface of the collapsed size. Folded. When deployed into a relatively high velocity mass of air, the hood or pocket first captures and captures a portion of the air surrounding that mass and directs this portion into chamber 14, thereby causing pylon 1 - the chute to become parachute. In the same manner as the peripheral cap is pulled into the airflow during the operation of the 02 132, it unfolds all of its folds and begins to unfold radially outward.

The star shape of chamber 14 provides very important advantages not available from other chamber shapes such as square or round. The lobes 32, which are arranged around a central longitudinal axis, therefore displace the air impact mass in a pattern that is similarly arranged between the lobes, thereby creating a balanced aerodynamic force about the indicated axis. occurs in a constant manner. This results in a self-correction of the position and direction of the bomblet 12's movement with respect to the impact plane of the target! ) Reduce wobbles, crashes, or unevenness in the flight path due to angular misalignment of the I mechanism, which would result in excessive scattering, unexploded or unexploded ordnance of the rocket's payload containing multiple small bombs Or minimize. 3
Satisfactory results might be achieved if more lobes were configured in the manner described above, but fewer than 3 (but not 3) would provide the necessary balance.
Only 3 is preferred.

The star-shaped chamber 1/1 provides a significant improvement over conventional reducers regardless of the shape or configuration of the bomblet 12, but as indicated by the splined or scalloped edges 19, the bomblet 12, it has been found to be particularly advantageous to step the lower end edge with non-uniform flatness. Thus, with reference to FIG. 5, arrow 64 indicates the path of movement of bomblet 12 during descent following deployment from a missile or projectile. Arrow 66 indicates the direction of free airflow with respect to bomblet 12. Dashed lines 68 and 70 indicate areas of separation between airflow masses of varying characteristics due to aerodynamic interference from bomblets 12. In this way, the sustained impact of the airflow 66 on the lower end 19 of the bomblet 12 always produces high turbulence, and the proximal surface 18, which begins with a uniform flow,
These flow conditions indicated by lines 68 and 70 result in a free air flow outside the mass of air characterized by these flow conditions.

Each of lines 68 and σ 70 can be seen close to surface 18 at vertically spaced locations, since turbulence effects occur where free airflow 66 first contacts edge 19. Because it begins. Accordingly, line 70 extends generally upwardly from the lowermost edge of downwardly projecting rectangle 22 and includes angle 72 enclosed by 18.
form. The line 68 extends from the same plane, but at a higher location, apparently at the top 25 of the space 24, forming an angle 74. Angles 72 and 74 are the same and their respective lateral distances from the vertical centerline 76 axially through the bomblet 12 are different. Distance 78 may be prominently shown to be longer than distance 11180. The star-shaped shape of Chi 17 Chamber 14 is designed using this flow phenomenon, because Chi 1? When the member 14 is sufficiently blinded, each day on its star shape projects so that it projects beyond the turbulent space in the manner shown by row 132 in FIG.
This is because the size of the outermost end of the tube is determined. Lobe 32 extends a radial distance from axis 76 by a distance 1i1t80 or more such that pocket 54
It is installed in the free stream region outside the turbulence region between 8 and 70.

The flow pattern thus suggested in FIG. 5 is illustrated in FIG. 6, which is a bottom view of FIG. 5 looking in the direction of arrow 66.

The dotted lines seen in FIG. 6, for example, indicate that the shape of the flow pattern resulting from splined contours 20, 22, 24 and 26 essentially follows the same contour or pattern as row 132. In this way, line 68 is
It corresponds to the portion of line 82 that is radially closest to central axis 76 . This pattern results from the splined profile of the lower distal edge of the bomblet 12 and, in combination with the star pattern of the chamber 14, produces a stabilizing effect that avoids spinning of the secondary charge 10. If the pocket 54 is inside the turbulent space fR region or frustoconical volume defined by the tanks 68 and 70, the chamber 14 will not bulge but will simply flap inefficiently.

FIG. 7 shows a graph of the effect of poor angle of impact on the lethality of bomblets 12, and FIG. 8 shows the angular parameters represented by the graph of FIG.

In FIG. 8, the reference numeral 94 indicates the target surface, which in some cases may be the ground, and in other cases may be the armored surface of the tank. The bomblet 12 may be a shaped charge for penetrating armor plates, an anti-personnel blast fragmentation device, or other signal detection or relay device, typically having several antennas in a symmetrical array. Contains payload format.

In fragmentation bomblets for anti-personnel use, the widest fragmentation dispersion for maximum effectiveness occurs when the bomblet 12 is substantially vertical at the moment it detonates, so that the blast effect is horizontal. be.

If a small bomb were to explode with the bomb first covered at an angle of 1, most of the blast effect and detonation would be dispersed upwards at an angle of 1, towards the sky, thus causing no damage or injury to anyone on the ground. I can't. Thus, if the vertical axis through the bomblet 12 is at an angle of 15° from the vertical plane, the lethality of the blast will be 60 degrees greater than the maximum that can be achieved with a vertical axis.
It is only %.

Similarly, for correct placement of the antenna of the main body 12 it must land with its central axis vertical.

Although no antennas are shown in the figures, it will be appreciated that any suitable antenna system, of which there are many known in the prior art, may be adapted to impinge on body 12. Similarly, no shaped charge is shown and the present invention does not depend on the selection of any particular such penetration system known in the prior art. However, in any such system,
It is extremely important that the central axis of the body 12 containing the shaped charge must be approximately vertical when driven through a substantially horizontal armor plating surface.
This is because an amorphous metal fuse formed by a shaped charge would not otherwise effectively penetrate such a plate. It is particularly important in the case of a crushing mechanism that the body 12 does not spin upon impact. The de-spin function of the chamber 14 is extremely effective because the rows 132 have fin-like aerodynamic properties that allow free airflow between the spaced ropes to This is because rotation around the central axis 76 in the figure is delayed.

Although only one exemplary embodiment of a device according to the invention has been described herein, numerous variations are possible within the teachings of this disclosure. It is the intention, therefore, to be limited not by the detailed description of the invention, but rather by the terms of the claims appended hereto.

[Brief explanation of drawings]

FIG. 1 is a general perspective view, partially cut away, of the configuration of the invention of the present application. FIG. 2 is an exploded view from FIG. 1 of the deceleration device partially disassembled. FIG. 3 is a cross-sectional view of the arrangement seen in FIG. 1, but with the reducer in a folded or folded position. FIG. 4 is similar to FIG. However, it does show a number of small bombs in an intricate relationship within the rocket. FIG. 5 is a side view of the arrangement seen in FIG. FIG. 6 is a diagram separated from FIG. 5 of this configuration. FIG. 7 is a graph illustrating the loss of combat effectiveness for the configurations of FIGS. 1-5 based on angular displacement. Figure 8 shows Figures 1 to 5 before colliding with the target.
FIG. 2 is a general diagram of the configuration from the figure. In the figure, 12 is a small bomb, 16 is a shaft, 30 is a load of 8 bars, 18 is a housing, 34 is a flat top panel,
36 is the bottom panel, 40 is the plate, 32 is the 0-b, 5
0 indicates a hole.

Claims (12)

[Claims] (1) An inflatable reducer for deployment in upper air currents with an attached loading unit comprising a plurality of lobes projecting radially outwardly in spaced relation to each other. a generally star-shaped inflatable, deflectably collapsible chamber, the chamber in the inflated state having an essentially flattened upper surface and a conically shaped lower surface. an air inlet means including at least one air passage proximate the outer end of each said lobe, and operatively associated with and overlying and spaced apart from each said air inlet. an inflating device comprising an upright hood and further comprising air suction means for capturing a portion of external airflow around the chamber and directing a portion thereof toward the inlet to inflate the chamber; A speed reducer that can. (2) further comprising: a payload body in the form of an elongate; and attachment means at one end of the body for securing the chamber to the body, the body having a lower end opposite from the one end; 2. A speed reducer as claimed in claim 1, wherein the reducer has a spline shape with notches between spaced apart projections, one of said projections being vertically aligned below each of said lobes. Machine. (3) the number of said lobes is three, and the protrusions are three, below each of the lobes, and the outermost end of each said lobe is such that free airflow is connected to said lower end; 3. A speed reducer as claimed in claim 2, which projects outwardly beyond the turbulence resulting from the contact. 4. The speed reducer of claim 2, wherein the payload body includes a generally cylindrical bomblet for fragmentation against a ground target. (5) The speed reducer according to claim 3, wherein the payload body includes a signal detection antenna array. 6. The speed reducer of claim 2, wherein the payload body includes a shaped charge for penetrating armored steel plates. (7) A combination deceleration and anti-spin device for attachment to a secondary munition having at least three radially extending lobes and having an essentially planar top surface and a conically shaped top surface when in the inflated state. an inflatable star-shaped chamber having a lower surface; air inlet means provided in each of said lobes proximate an outermost end thereof; operatively associated with each said air inlet means; an air suction comprising an upright hood around and spaced from said inlet means to capture a portion of external airflow around said chamber and direct that portion toward said inlet to inflate said chamber; A device with means. (8) The inflatable star-shaped chamber comprises:
Prior to deployment into the upper airstream, the lobes are constructed and arranged so that they are tightly folded and stacked to form a densely compressed compact size within the minimally spaced container possible. 8. The apparatus according to claim 7. (9) The highly compressed and compact dimensions are constructed and arranged in very tightly nested relationship and tightly fitting with the concentrically formed cavity in the center of each submunition. , the apparatus according to claim 8. (10) Due to the discharge of the deceleration and anti-spin device into the upper air stream, the compressed compact size is expanded by internal pressure and the chamber decelerates and stabilizes the secondary munition. 10. The device of claim 9, wherein the device is inflated to (11) Upon deployment into the upper airstream, first capture and capture a portion of the air surrounding the compact size, and direct this portion of air into the chamber to unfold and unfold all of the lobes. The chambers are folded and stacked in such a manner that one or more hoods are exposed on the outer surface of the folded dimensions to begin to expand radially and outwardly to inflate the chambers. , the apparatus according to claim 10. (12) The lobes are constructed and arranged about a central vertical axis so that when air impinges on the lobes, a balanced aerodynamic force about said central vertical axis results in self-correction of the position and direction of movement of the secondary munition. 8. The apparatus of claim 7, which reduces and minimizes wobbles, crashes or unevenness in the flight path.