JPH01249685A - Propellant charge and production thereof - Google Patents

Abstract

PURPOSE: To make it possible to a smokeless or min. smoke quantity propellant charge which burns sufficiently rapidly, by forming the coatings of solid propellant materials on the ligaments of a network supporting material to such a thickness at which specific gaps exist.

CONSTITUTION: The propellant charge for a motor grain, such as launch motor or flying motor, comprises a networks structure 50 and the ligaments 52 thereof are coated with the suitable propellant materials (coatings) 54. The thickness 56 of the coatings 54 is so determined that the gaps to determine the surface regions 60 of the propellant for the purpose of combustion exist between the coated ligaments 52 in order to increase the surface areas thereof.

COPYRIGHT: (C)1989,JPO

Description

DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention relates to solid propellant charges. Applications of the propellant charge of the present invention include launch ejection motors where it is desired that the propellant charge burns rapidly to rapidly develop heat or thrust.
ors) and igniters. Other uses for the propellant charge of the present invention include as a gas generator for vehicle air bag inflation and other devices where rapid production of inflation gas is desired. Some use it as a gas generator. Therefore, for purposes of this specification, "propellant charge" includes gas generators for air bag inflation devices and other inflation devices. However, it should be understood that the invention is not limited to just these uses, but will find use in a variety of applications, such as as a propellant charge for the main propulsion of a rocket motor reservoir. .

PRIOR ART AND PROBLEMS SOLVED BY THE INVENTION A typical solid propellant charge includes a fuel such as aluminum particles and an oxidizing agent such as ammonium perchlorate; They are bonded together by a binder such as hydroxy-free & 4% IM polybutadiene. The binder may also act as a fuel. When the fuel and oxidizer are separate substances that are mixed together to form a propellant, the propellant is called a "composite propellant."
) is known as j.

Mixed propellants are usually made by blending the components into an aly and viscous but still flowable mixture, then adding it to the rocket motor chamber, and pouring this mixture into position for use. Manufactured by curing into a solid mass of propellant. For some applications, such as igniters and air bag flakes, the propellant mixture may be extruded, e.g., US Pat. No. 4,547 to Adams et al.
It may be of any desired geometry, such as a bellet for an air bag inflator as exemplified at No. 342, No. 62.

In solid propellant charges, combustion proceeds exactly perpendicular to the surface. Therefore, the propellant grains are holed (
In a type of rocket motor known as an end burner, which is a solid mass of propellant without perforation, combustion begins at the nozzle end and proceeds toward the head end of the rocket. The burn time of end-burner propellant grains is relatively slow compared to propellant grains that are vertically perforated, generally along a longitudinal centerline.

With this type of grain, combustion would likely begin along the entire length of the propellant grain, so that combustion would proceed radially outward from the hole toward the rocket motor case. The combustion time of the propellant charge is also determined by the shape of the internal bore, [tube 5hap]
e) J or “center perfora”
te) The shape known as J is e.g.
ape) burns relatively slowly than the shape known as J.

Tactical weapons, such as canister fired missiles, may use a launch ejector motor containing a solid propellant charge to eject the missile from the canister before igniting the main motor. Any large amount of smoke or exhaust containing toxic gases may be harmful to personnel, and the smoke or exhaust must be maintained to control the missile after launch. Because visibility may be undesirably obstructed, neither the propellant charge for the launch ejection motor nor the propellant charge for the flight motor igniter should be smokeless or minimum smoke-free.
moke) type is preferable. However, smokeless or minimal smoke propellants generally do not burn as quickly as is typically desired. Additionally, it tends to soften at the high temperatures this type may encounter. The propellant becomes so soft that its physical state becomes
If the acceleration changes while the missile is being ejected from the canister, the burn characteristics of the propellant will change accordingly, possibly resulting in an inappropriate burn rate or possible detonation of the launch ejector motor. do.

The preparation of solid propellants consisting essentially of a cellular fuel element having homogeneous interconnecting spherical voids of a metal or alloy and a propellant material filling the voids is described in US Pat. This is suggested in the specification of Japanese Patent No. 3191535.

It is also clear from Walz that molded articles containing networks of metals or of the expanded variety can be used as solid propellant reinforcements and burn rate modifiers.
) U.S. Patent Nos. 3,616,841 and 3,946
No. 039 specification. These Waltz patents, which are hereby incorporated by reference and made a part of this specification, describe such networks with pores ranging from 3 to 1 per linear inch.
Manufactured using a self-supporting reticulated polyurethane or ligament-formed cellular foam as a mold to give a substantially homogeneous network structure which may be of a wide range of pore sizes varying up to 25 mm. We describe a method to do so, and the finished cellular material is characterized by having ligaments that are continuous, gas-free or have low porosity, and are of monolithic construction.

U.S. Patent No. 432122 for Camp
No. 0 discloses a method of strengthening a propellant charge by embedding support structures into the propellant charge. This method allows the flexible perforated material to be attached to the desired deviceff1f
It is disclosed as comprising slowly traversing the propellant lacquer until fl is obtained. Camp says that the "reinforced" support is perforated or its extension-like form so that it is "permeable to the decomposition gases of the propellant that it releases during storage," and that it is also rigid. and low density.

Although Camp states that a "strengthened" propellant should have a "watzful-like appearance" so as to have "desirably increased surface area," the disclosure in Camp's specification indicates that the propellant poses the problem of increasing the strength of the propellant charge, and while the "Watzful-like appearance" is a step in the right direction, it still provides a smokeless or minimal smoke propellant charge that burns sufficiently rapidly. There isn't. The Woltz patent does not disclose increasing the surface area of the propellant charge to achieve faster combustion, and therefore does not provide an adequate answer to the above problem.

It is therefore an object of the present invention to provide a smokeless or minimal smoke propellant charge that burns quickly, ie has a fast burn time. "Burn time" refers to the time required to burn a particular volume of propellant charge, and it varies according to the type of propellant as well as the physical shape of the propellant charge. In contrast, the "burn rate" perpendicular to the propellant surface is constant for a particular propellant material.

(IL propellant material) It is an object of the present invention to provide smokeless or minimally smoked ?lII propellant grains or charges which are also capable of withstanding strong acceleration forces even when they have a softening profile at high temperatures. This is another purpose of

One proposal for a solution to the problem of slow burn times of smokeless or minimal smoke F11 propellants is to add burn rate catalysts, such as lead and/or copper salts, to the propellants to control their ballistic behavior. The goal was to increase their burning rate.

However, because of the activity of such additives, it is also desirable to eliminate them from propellant cheats. Accordingly, it is yet another object of the present invention to provide a smokeless or minimal smoke propellant charge that reduces burn time but does not contain such toxic materials.

The igniter propellant material, consisting of boron and potassium nitrate pellets, is placed in a housing such as a perforated tube or wire bolt so that propellant gas from the igniter can pass through the Tll propellant grains to ignite the propellant grains. must be placed in Such a perforated tube or tube may become blocked or blown out during the ignition phase, both of which situations do not affect the safety of the rocket. It is another object of the invention to eliminate such a basket or tube for the igniter and thus reduce its cost.

It is a further object of the present invention to provide an automotive air bag inflator that is capable of utilizing a gas source propellant charge with reduced burn time.

It is another object of the present invention to reduce the risk of untangled propellant charges resulting from shock waves or electrostatic discharges.

It is yet another object of the invention to reduce the burn time of a propellant charge.

It is yet another object of the present invention to provide a fast burn time propellant charge that is safe, reliable, and non-toxic.

The above and other objects, features, and advantages of the invention will become apparent from the following description, which details preferred embodiments of the invention and should be read in conjunction with the accompanying drawings.

[Means for solving problems, examples, and effects]

Referring to Figure 1, shoulder firing
A canister-launched missile is shown at 10 and includes a launch ejection motor 12 and a flight motor 14.

Launch ejection motor 12 is used to eject a flight motor 14, typically from about 10 inches (about 250 mm) to about 6 feet (about 1.8 m) in length, from a canister (not shown). The flight motor 14 is a solid propellant motor that is then ignited when the flight motor 14 is at a safe distance from the operator. The size of the launch ejector motor 12 is related to the size of the flight motor. 40 inches long (
For a 1016 mm) flight motor, the length of the launch ejection motor may be approximately 4 inches (approximately 100 mm).

Referring to FIG. 2, firing motor 12 includes a generally cylindrical case 16 and a nozzle 18. Referring to FIG. 2
At 1 there is shown an electric match or initiator, commonly known as a squib, which is ignited by an electrical conductor 22 passing through a conventional nozzle plug 20 and into the nozzle opening. Igniter 24 ignited by squib 21
releases hot gas onto the surface of the launch motor propellant Dallaine, shown at 28, to begin its combustion. canister
After flight motor 14 is ejected from (not shown), any suitable separation device, generally exemplified at 30, includes the launch ejection motor 12, a forward closure 31, and a conventional separation piston 23. Separated from the launch motor. The forward closure 31 is removably retained on the flight motor case structural member 32 by pins 25 spaced circumferentially. Retaining ring 27
holds and aligns the front closure in place.

Such separation devices are of conventional design and can be constructed using engineering principles generally known to those skilled in the art to which this invention pertains, and therefore will not be described in further detail herein. will not be explained.

To explain with reference to the third part, the flight motor 14 is
- includes a cylindrical case 32, which case 32 includes a head end 34, from which the case 32 extends rearwardly to a nozzle 36, the nozzle 36 being molded; or otherwise suitably attached to support member 37, which in turn is sealingly attached to the case wall by lock ring 39 and O-ring seal 41 (FIG. 2). Contained within the case 32 is a propellant charge 38, which is ignited by an igniter 40. Disposed between propellant charge 38 and case wall 32 is a layer of suitable insulator 42 and a suitable inhibitor 43.

The igniter 40 is electrically ignited by a conductor 45 passing through a through bulkhead connector 47 ] or by two or more squibs 44 . A suitable conventional ignition interlock 4 to prevent accidental or
8 is prepared and missile 10 is a canister (not shown)
Prevents squib 44 from being ignited until after it is released from W
do. wire for conventional lanyard assemblies
) is illustrated at 46 and passes through an ignition ink-lock illustrated at 48 which also serves as a nozzle closure.

The possibility of a propellant charge 28 for the launch ejector motor 12 and an igniter 40 for the flight motor 14 are of conventional design for the missile 10 and are generally understood by those skilled in the art to which this invention pertains. It can be constructed using known engineering principles, and therefore the conventional parts of missile 10 need not be described in further detail.

Referring again to FIG. 2, smoke or exhaust fumes from the launch motor nozzle 18 that may be detrimental to the manipulators and obstruct visibility of the target after launch necessary to control the missile. To prevent the release of
such as a propellant material containing 0% by weight and 1% by weight of a stabilizer (such as N-methylnitroanaline to scavenge nitrate ester precipitation products).
Contains minimal smoke propellant material.

To reduce smoke during the ignition phase of the flight motor 14, the igniter 40 for the flight motor 14 also contains, for example, 47% by weight nitrocellulose, 48% by weight nitrate ester plasticizer, processing aids (viscosity modifiers), etc. 4% by weight) and 1% by weight of stabilizer.

Many propellants can produce water vapor clouds at sea level, but when burned at or near sea level (
Canister-launched missiles are usually launched at such locations) The propellant, which produces large amounts of smoke, is a significant amount (i.e. 2
0% by weight or more) of chloride-forming compounds such as ammonium perchlorate (which produces hydrogen chloride); and/or significant amounts (i.e. 10% by weight or more) of aluminum. Contains metals such as.

If the propellant contains more than approximately 5% by weight of metal salts (commonly used as burn rate catalysts), large amounts of smoke may also result.

Therefore, for purposes of this specification, "minimum smoke amount"
Propellant or propellant material is defined as a propellant or propellant material containing 0-20% by weight chloride-forming compound, 0-10% by weight metal, and 0-5% by weight metal salt. .

Compared to other rocket motor propellants, minimal smoke propellants do not burn very quickly. However, to increase the combustion rate of igniter 40 or launch motor brain 28, lead and/or
Alternatively, the addition of copper salts is not considered desirable due to the toxicity of such burn rate catalysts.

Minimum smoke volume to reduce the burn time of the propellant charge for the igniter 40 and launch motor grain 28 without adding a combustion rate catalyst and also to eliminate the basket or tube housing for the igniter pellet. The igniter 40 is used to strengthen the propellant charge so that it can withstand the acceleration forces during firing.
The propellant charges for the and launch motor grains 28 are each constructed in accordance with the present invention from a reticulated structure illustrated at 50 in FIGS. 4 and 5, and their ligaments 52 are made of a suitable propellant material 54. The coated ligaments are coated such that gaps exist between the coated ligaments to increase surface area as will be explained more fully below. As shown in FIG. 4, where a reticulated carbon is illustrated, the reticulated structure 50 includes a number of ligaments 52 that are generally of uniform size and interconnected to form interconnected pores.
It consists of For the purposes of this specification, a "network structure" or "network support" refers to a structure or substrate that is composed of a number of ligaments that interconnect with each other to form pores that communicate with each other. is meant as applicable, and as such includes structures such as those described in the Woltz patent.

To prevent or reduce the generation of smoke from combustion of the network 50 in accordance with aspects of the present invention, materials that do not combust at the temperatures and conditions at which the coated propellant of both the launch motor grain 28 and the igniter 40 will combust, or a minimum Each is composed of smoke amount materials. Although carbon and graphite may be combustible under certain conditions, such as when the propellant material is oxygen-rich, carbon and graphite produce carbon dioxide without smoke when they burn; Therefore, it is the material with the least amount of smoke.

Other applications of the coated network of the present invention may not require the propellant charge to be of the smokeless or minimal smoke or reduced smoke type, in which case the network 50 may also It may also be preferable to construct the propellant material from a combustible material, such as aluminum, boron, beryllium, or copper, so that it combusts and increases energy when it is combusted. in this way,
It should be understood that the network structure 50 of the present invention is not limited to minimal smoke or non-combustible materials.

Ligament 52 may be dimensioned such that network structure 50 only occupies between about 1.5% and 6% of the volume of the propellant charge. The propellant material coating 54 is well known to those skilled in the art to which this invention pertains.
Any suitable method may be used, such as by blowing or dip coating the ligament with a propellant lacquer prepared by dissolving the propellant material in a suitable solvent such as acetone, and then drying this material on the ligament. It may be applied to the ligament 52 by means. Coating 54,
The thickness illustrated at 56 in FIG. 5 is determined by applying engineering principles generally known to those skilled in the art to which this invention pertains to achieve the desired impact performance and other required performance. . However, in accordance with the present invention, the thickness 56 of the coating 54 is such that there is a gap, illustrated at 58, between the interconnecting coated ligaments, and the propellant for combustion is A surface area 60 is defined. Several dip coating or spraying and drying operations are repeated to build up the propellant material to the desired thickness.
It may be necessary to attach up to 6. This thickness may be so small that it is almost impossible to penetrate the gap 58f)l' with the naked eye, so that, taking into account the volume occupied by the network 50, the propellant The available volume of the charge is probably 90~
Although a very large proportion of 97.5% is occupied by propellant material, the surface area 60 for rapid combustion will nevertheless increase, perhaps to the order of 500x or more.

Referring to FIG. 6, there is shown generally at 70 a gas generator or inflator assembly according to the present invention for generating gas to inflate an inflatable crash bag of a vehicle. The inflator 70 has a generally cylindrical outer shape and includes a housing structure 72 that includes two structural members.
Contains.

These two structural members are the upper sl.
+e1. l) or differential user-74 and lower outer i (lo
5hell) or base 76, which are joined by three concentric friction welds indicated at 78, 80, 82,
Forming the housing structure 72 of the inflake-build 70. The three friction welds are performed simultaneously in a single friction welding operation.

The differential user 74 has three concentric cylinders 84,
It could be made by forging along with 86 and 88.

Each of these cylinders is a differential user-74
extend downwardly from a common flat top wall 90 to form separate weld interfaces with the base 76.

Inner cylinder 84 cooperates with top wall 90 and base 76 to form a cylindrical ignition chamber 92 .

The middle cylinder 86 is connected to the inner cylinder 84 and the upper wall 9
0 and the base 76 form an interior chamber, specifically a combustion chamber 94, having the shape of a toroid.

The outer cylinder 88 is connected to the middle cylinder 86 and the upper wall 9
0, and the base 76 form an outer chamber 96 which also has the shape of an L.roid. cylinders 84 and 86 respectively.

88 each include a plurality of regularly spaced exhaust openings or outlets 98. 100, 102 through which the generated or inflation gas flows into a protective air hassog (not shown) to be filled.

The base 76 includes a flange 104 that is used to attach the inflator assembly 70 to the vehicle whose occupant is to be protected.

Disposed within the ignition chamber 92 is an igniter charge assembly 105 (z3) comprising a rupturable sealed aluminum container 106 containing an ignitable substance 108.

The container 106 may be sealed against moisture, has a depression or cavity 110 formed in its bottom 111 and is retained within the ignition chamber 92 by a retaining ring 112. The retaining ring 112 has a shape that matches the bottom 111 of the container 106, including the recess 110, and it will be inserted into the end of the ignition chamber 92 by a press fit. Container 106 is held at its two ends spaced apart from the inner surface of top wall 90 by cushion/spacer material 114, which may optionally include seraphibar material.

Although various pyrotechnic materials may be used as the igniter, the preferred material is a granular mixture of 25% boron and 75% potassium nitrate by weight.

This mixture was found to combust with a very hot flame suitable for igniting the solid fuel gas generating material used in the inflator assembly 70 as described below.

In the recess 110 of the container 106, an igniter 11 is placed.
6 is included. The igniter 116 has a conically shaped lower portion and is mounted in a hole 118 having a mating conically shaped upper portion as shown. A hole 118 is provided at the center of the base 76.

The igniter 116 is held at two ends of the hole 118 by a crimp 120 formed in the base 76, which overlaps and connects with the conical top of the igniter 116.

The igniter 116 may be a conventional electrical squib having a pair of energized electrical terminals (not shown) adapted for a bayonet connection to external collision detection means (not shown).

So that suitable propellant materials with lower burning rates can be used to generate the gas according to the invention,
To obtain rapid burn times for slow burn propellant materials, a mesh structure 50 similar to that of FIG. 4, preferably constructed of minimal smoke or non-flammable materials such as carbon or graphite A generally donut-shaped propellant charge 122 comprising a reticulated structure and coated with a suitable propellant material, preferably a minimum smoke propellant as described above, is
- It is placed inside the Lloyd-shaped combustion chamber 94.

The propellant charge 122 is surrounded by an annular inner screen puncture or combustion chamber filter 124. Inner screen back 124 may include a layer of roughened screen 126 adjacent the inner surface of concentric cylinder 86, if desired. An aluminum washer-shaped retaining ring or disc 128 holds the propellant charge 122.
and the inner screen back 124 in place;
and keep them separate from the base 76 during the friction welding operation.

The inner surface of the base 76 includes a rounded annular ridge 130. This ridge 130 serves to reduce the free volume of the combustion chamber 94. Additionally, ridge 130 provides support for retainer plate 128 while inflator assembly 70 is in operation.

An aluminum turning ring 144 is provided within the outer toroid-shaped chamber 96. The turning ring 144 is made with an inwardly directed curved flange 146 at its upper end and has a plurality of adjacent uniformly spaced exhaust openings or vents 0148 at its lower end. The length of the deflection ring 144 is at least as long as the concentric cylinder 86, and the deflection ring 144 is press-fitted into contact with the outer surface of the cylinder 86 at its inner Ti:i portion and also at its outer end. Welded flashing (eng.
aging + ueldflashiB) 140 and is placed in position in conjunction with the cylinder 86. Also included within the coid-shaped chamber 96 is an outer screen bank or filter 150.
I:, it is. Screen puncture 150 may include hulls 152 adjacent the inner surface of cylinder 88, if desired.

The functioning of the inflation assembly 70 is initiated by an electrical signal from a crash detector (not shown) to the igniter 116. The igniter ignites and projects into a sealed aluminum container 106 holding an ignitable material 108. Ignition IJ! /J material 108 burns and explodes through the wall of container 106 and into the cylinder 84.
through an outlet opening 98 into the toroid-shaped combustion chamber 94. The hot eveninger gas ignites propellant charge 122 which releases inflated gas. These gases flow through the inner screen back 124 and radially outwardly through the combustion chamber outlet opening 100. Screen pack 124, Infu I/
- Helps cool the Targus and remove more particulate residues. As the gases exit the combustion chamber opening 100, they are redirected downwardly by the deflection ring 144, where they impinge on the flashing 140 from the intermediate cylinder friction weld 80. Flushing 140 serves to disrupt gas flow and further remove particulates from the exhaust gas. The inflation gas then flows radially outwardly through the opening 148 in the turning ring 144 toward the annular space between the turning ring 144 and the outer screen back 150 and through the outer screen puncture 150 to the final radially outwardly through the outlet aperture 102 .

The outer screen bank 150 further serves to cool the exhaust gas and remove particulate matter.

More detailed information regarding such inflation is contained in the aforementioned patent specification to Adams et al., which is hereby incorporated by reference and herein incorporated by reference.

Of course, it should be recognized that the Adams et al. patent discloses the prior art Vereso I. rather than the coated network of the present invention as comprising the propellant charge.

To prepare a propellant charge in accordance with the present invention, a network 50 is first prepared by the method described in the Waltz patent, or by any other suitable method. The elongated structure 50 of Ligamen 1-52 is then coated with a suitable solid propellant material 54 as previously described by dip coating, spraying, or any other suitable coating method; It may be necessary to do this several times as discussed above. The one or more coatings of solid propellant material 54 are then dried on the ligaments 52 while maintaining gaps 58 between the coated ligaments that define propellant surface areas 60 for combustion.

The resulting propellant charge may be configured as a rocket motor propellant or igniter, or as a gas generator for an air bag, or by other means utilizing principles generally known to those skilled in the art to which this invention pertains. It can be used for appropriate purposes. For example, a propellant charge embodying the present invention for an igniter, such as igniter 40, may be secured to a suitable structural support of a rocket motor (not shown) by utilizing a set of screw threads (not shown). may be conveniently attached to or combined with,
A propellant grain, such as grain 28 embodying the present invention, could be conveniently coupled to a case, such as case 16 of a rocket motor.

By way of example, embodiments of the present invention may be applied to phantom triol (B i' TN
) and nitrocellulose (NC) were dip coated and tested on reticulated carbon.

The data below is 45i per inch (25.4mm)
The sample was prepared by dip coating a 50150 (w/w percent) acetone solution of BTTN/NC (50 x) on a 11 J porous reticulated carbon sample.

Typical burn times at 100 Or + ξ' (: (70 kg/c) for conventional solid form propellant materials without voids tested below are approximately 0.2 inches/second (approximately 5.1 mm/second). s) and approximately 0.4 inches/second (approximately 10.21
1/S). Thus, test results indicate that a propellant charge comprised of propellant materials and embodying the present invention will achieve burn times that are several times greater than the typical burn times of propellant materials. shows. A sample of the propellant charge tested was prepared and combusted in a window bong to produce a large amount of subsurface combustion (
subsurface combusl. ion) (i.e. combustion inside the coated network) was observed.

If the network structure 50 is non-flammable, the structure that remains after combustion may serve as a combustion stabilizer by damping pressure waves or sound waves, and may serve as a means to break up vortex formation in the gas flow. do not have. Additionally, a carbon network may be primed on the motor case to prevent electrostatic discharge hazards.

The total surface area available for combustion in a coating 1'14-like structure embodying the present invention is so large that, if such a coating network is provided, the burning rate of the propellant material coated thereon will be significantly reduced. Fast burn times are achieved no matter what.

It is understood that the invention is in no way limited to the particular embodiments illustrated and described herein, and that various modifications may be practiced that fall within the scope of the invention as defined by the claims. You should understand that you will be able to do so.

[Brief explanation of the drawing]

FIG. 1 is a cross-sectional view of a canister-launched missile embodying the present invention, with -f(1;) of the case broken and removed. FIG. Figure 3 is a partial cross-sectional view in a longitudinal plane of the flight motor of Figure 1. Figure 4 is a partial cross-section of the flight motor of Figure 1. 5 is a perspective view of a portion of a network structure of a solid propellant charge embodying the invention. FIG. Fig. 6 is a partially enlarged view of a gas bag inflator embodying the present invention.
FIG. In the figure, 10 is a canister-launched missile, 12 is a launch motor, 14 is a flight motor, 16 is a launch motor case, 21 is a squib, 28 and 38 are propellant charges, 3
2 is a flight motor case, 36 is a nozzle, 40 is an igniter, 50 is a network structure, 52 is a ligament, 54 is a coating, 56 is a coating thickness, 60 is a surface area, 70 is an inflator-174 is a diffuser-17
6 is a base, 92 is an ignition chamber, 94 is a combustion chamber, 96 is an outer chamber, 108 is an ignition substance, 116 is an igniter, and 122 is a propellant charge. Margin procedure ζ11 Right and wrong (method) Jul. 11, 1988 Commissioner of the Japan Patent Office Yoshi 11:1 Moon Takeshi 1, Indication of the case 1988 Patent application No. 076635-2 Name of the invention Propellant charge and its Manufacturing method 3, relationship with the case of the person making the amendment Patent applicant name Mo 1 Hen Thiokol. Inchoraidito 4 agent address: Shizuka Toranomon Building, 8-10 Toranomon-chome, Minato-ku, Tokyo, 105 Tel: 504-07215, for amendment order]
Date of June 28, 1983 (Shipping port) 6. Drawings to be amended 7. Contents of amendment: Cleaning of the drawings (no change in content) 8. Inventory engraving drawings of accompanying documents 1 copy Procedure amendment form 1988 3/ IEI Director General of the Japan Patent Office Yoshi 1) Takeshi Moon 1, Indication of the case 1988 Patent side No. 076635 2, Name of the invention Propellant charge and its manufacturing method 3, Person making the amendment Relationship with the case Patent applicant name: Morton Thiokol. Incoholity 1-4, Agent address: 8-10-5 Shimome, Toranomon, Minato-ku, Tokyo 105
Subject of amendment (1) “Claims” column of the description (2)
Column 6 of "Detailed Description of the Invention" of the Specification, Contents of Amendment (1) The scope of claims of the specification will be amended as shown in the attached sheet. (2) (a) Add "55" between "pore" and "form" on page 20, line 3 of the specification. (0) On page 26, line 7, “it” is replaced with “crimp 120”.
” he corrected. 7. List of attached documents Claims 1iim2. Claims 1. AJi with multiple interconnected ligaments
an l-shaped support shrine and a coating of solid propellant material on the ligament, the thickness of the coating being:
The propellant charge is of such thickness that between the coated ligamens there are gaps defining the surface area of the propellant for combustion. 2. The net support material has a minimum smoke volume.
2. The propellant charge of claim 1, wherein the propellant charge is comprised of a material selected from the group consisting of moke)+, tts+, and non-flammable materials, and wherein the solid propellant material is a minimum smoke propellant. 3. The propellant charge according to claim 1, wherein the reticular protrusions are composed of a material selected from the group consisting of carbon and graphite. This method of manufacturing a propellant charge comprises the following steps: 4. Providing a reticulated support having a number of interconnected ligaments; b. Coating this ligament I- with a solid propellant material. and maintaining the thickness of the C6 coated coating to such a thickness that there are gaps between the coated Liganone I layers that define the surface area of the propellant for combustion. A method comprising:

Claims (1)

Claims: 1. A reticulated support having a number of interconnected ligaments and a coating of solid propellant material on the ligaments, the thickness of the coating being such that the thickness of the coating is between the coated ligaments. The propellant charge is of such thickness that there is a gap that defines the surface area of the propellant for combustion. 2. The net-like support material has a minimum smoke amount (minimumsmo
The propellant charge of claim 1, wherein said solid propellant material is a minimum smoke propellant, and wherein said solid propellant material is a minimum smoke propellant. 3. The propellant charge of claim 1, wherein said reticulated support material is comprised of a material selected from the group consisting of carbon and graphite. 4. The propellant charge according to any one of claims 1 to 3, which is used as an igniter. 5. Canister-launched missile (canisterfi)
redmissile) used for the launch motor.
A propellant charge according to any one of claims 1 to 3. 6. Any one of claims 1 to 3 used as an igniter for igniting a propellant crane of a flight motor of a canister-launched missile.
Propellant charge as described in Section. 7. Used as a gas-generating charge for an inflator that generates gas for inflating an inflatable impact protection bag of a vehicle, which can be actuated by ignition to produce gas and combustion products, claim 1. 3rd from term
The propellant charge described in any one of the preceding paragraphs. 8. The propellant charge of claim 7, wherein propellant material occupies at least 90 percent of the volume of the gas generating charge. 9. A method for manufacturing a propellant charge, comprising the steps of: a. providing a reticulated support having a number of interconnected ligaments; b. coating the ligaments with a solid propellant material. ,
and c. maintaining the thickness of the applied coating at such a thickness that there are gaps between the coated ligaments that define the surface area of the propellant for combustion. 10. The step of coating the ligament comprises dip-coating the ligament with a propellant lacquer prepared by dissolving a solid propellant material in a solvent, and further drying the dip-coated ligament. 10. The method of claim 9, comprising: 11. The method of claim 9, wherein the step of coating the ligament comprises spraying a propellant material dissolved in a solvent onto the ligament and drying the spray-coated ligament. Method. 12. The method of claim 9, further comprising: constructing the reticulated support material from a non-flammable or minimal smoke material; and constructing the solid propellant material from a minimal smoke propellant. .