KR100388334B1 - Hybrid inflator with coaxal chamber - Google Patents

Abstract

The composite expander of the present invention includes an inflator housing and a gas generator housing containing a pressurized medium. The gas generator housing is connected with the inflator housing. The gas generator housing supplies a first chamber containing a propellant, a propellant ignition assembly, an inflator housing for combusting the propellant gas produced by the propellant ignited by the pressurized medium, and a pressurized medium from the second chamber towards the airbag. And an outlet arranged on the gas generator housing, and a first sealing disk which normally blocks the outlet and ruptures after ignition of the propellant. The first chamber, the second chamber, and the first sealing disk are arranged in common with the longitudinal axis of the expander. The gas generator housing includes at least one supply hole for maintaining the same internal pressure of the inflator housing and the first chamber.

Description

HYBRID INFLATOR WITH COAXAL CHAMBER

The present invention is part of a series of US patent application Ser. No. 08 / 389,297 filed Feb. 16, 1995 entitled "Synthetic Expander with Flow Initiation Assembly Based on Rapid Pressurization," which is dated October 25, 1994. A portion of US patent application Ser. No. 08 / 328,657, filed with the name "synthetic inflator and associated propellant", which is part of US patent application Ser. No. 08 / 210,668, filed March 18, 1994 with the name "synthetic expander." It is a continuous application.

FIELD OF THE INVENTION The present invention relates to the field of automatic inflation safety devices, and more particularly to synthetic inflators using rapid pressurization to initiate flow to an airbag or safety vessel.

Advances in inflator for automatic inflation safety devices have led to the development of pressurized gas expanders, propellant expanders and composite expanders. Of course, designs have been made in consideration of the inflators of the respective types described above. In these three inflators, two design considerations are that the airbag or safety bag must be inflated by a predetermined amount for a predetermined time to operate efficiently.

In recent years, the weight of the inflator is also an important consideration, because in many cases the weight of the vehicle is an important design consideration. In addition, due to the limited space available in many automotive designs, the size of the inflator is also an important design consideration.

It is therefore an object of the present invention to provide a synthetic inflator capable of rapidly mixing a propellant gas with a pressurized medium and rapidly combusting a mixture of the propellant gas and a pressurized medium under pressure to expand the airbag.

To achieve this purpose, the composite expander of the present invention includes an expander housing comprising a pressurized medium and a gas generator housing. The gas generator housing is connected with the inflator housing. The gas generator housing includes a first chamber containing a propellant, a propellant ignition assembly, a second chamber, an outlet, and a first sealing disk. The second chamber is in fluid communication with the first chamber and the expander housing to combust the propellant gas produced by the propellant ignited by the pressurized medium. The outlet port is arranged on the gas generator housing for supplying the propellant gas from the second chamber toward the air bag or safety bag. The first sealing disk blocks the outlet vertically and ruptures after combustion of the propellant. The first chamber, the second chamber, and the first sealing disk are arranged coaxially with the longitudinal axis of the inflator. The gas generator housing includes at least one supply hole to maintain the same internal pressure of the inflator housing and the first chamber.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. In this regard, the present invention relates to a composite inflator for an automatic inflation safety device. That is, the present invention relates to an expander utilizing stored pressurized gas and gas or heat generating propellants. Various types of synthetic expanders are disclosed in US Patent Application No. 5,230,531 to Hamilton et al., Assigned to the assignee of the present application, which is generally related to the present invention.

1 shows one embodiment of the automatic inflation safety device of the present invention. The main elements of the inflatable safety device 10 include a detector 14, an inflator 26 and an air bag or safety bag 18. When the detector 14 detects the condition necessary for the inflation of the airbag or gasbag 18 (ie, the predetermined deceleration), gas or conduit 22 from the inflator 26 toward the airbag or safety bag 18 through the conduit 22. A signal is sent towards inflator 26 to release other suitable fluid.

The inflator 30 shown in FIG. 2 is a synthetic inflator, which may be used in the expandable safety device 10 of FIG. 1 instead of the inflator 26. Thus, the inflator 30 includes a gas generator 82 as well as a bottle-shaped inflator housing 34, which inflates the pressurized medium supplied to the airbag or safety bag 18 (FIG. 1). And a gas generator 82 supplies a propellant gas to increase flow towards the airbag or safety bag 18 (e.g., inflate the pressurized medium 36 or additional product gas). Casing-type propellant (eg, hot fuel propellant) may be used to describe the propulsion granules located in the gas generator 82, as will be explained in more detail below. A mixture of gas (eg argon) and oxygen may be used for the pressurized medium 36. According to at least one feature associated with the present invention, the pressurized medium preferably comprises about 70% to 92% inert fluid and about 8% to 30% oxygen on a molar basis, more preferably about 79% To 90% inert fluid and about 10% to 21% oxygen.

The inflator housing 34 and the gas generator 82 are coupled to each other in a manner that is located inside the inflator housing 34 of the gas generator 82 to reduce the space required for the inflator 30. In particular, hollow diffuser 38 is welded to one end of hollow boss 86 (eg, having a diameter of about 1.25 inches (3.175 cm)). The diffuser 38 may have a plurality of rows of heat discharging holes 40 (e.g., 80 discharging holes 40) each providing a "non-propelled discharge" from the inflator 30, each about 0.100 inches (0.254 cm) in diameter. Having a screen 58 is positioned adjacent to the discharge hole 40. A sealing disk 70 is suitably positioned in the boss 86 and the sealing disk 70 is welded to this boss to initially hold the pressurizing medium 36 in the inflator housing 34. If it is desired to release the pressurized medium, the projectile 50 with the conical head is propelled through the sealing disc 50. In particular, the projectile 50 is located on the convex surface of the sealing disc 70 within the barrier 54 and the initiator when the inflatable safety device 10 (FIG. 1) is received from the detector 14. The projectile 50 is propelled by the operation of 46. A ring 62 is provided to initially hold the projectile 50 in position prior to ignition.

Orifice sleeve 74 is welded to the end of sealing disc 70 or boss 66. The orifice sleeve 74 is hollow and orifices allow fluid to flow through the interior of the inflator housing 34 and the boss 66 of the diffuser 38 when the sealing disc 70 is ruptured by the projectile 50. Holes 78. For example, four holes 78 each have a diameter of about 0.210 inches (0.53 cm). In addition, the inflator housing 34 and the gas generator 82 are connected to each other. To that end, a gas generator 82, in particular a gas generator housing 86, is welded to the orifice sleeve 74.

The gas generator housing 86 houses a number of propulsion pellets 90 which supply heated propellant combustion gas to increase flow towards the airbag or safety bag 18 (FIG. 1) upon ignition. The propulsion granules 90 are held in the gas generator housing 86 by a propulsion sleeve 94, the propulsion sleeves being the ends of the gas generator housing 86 by a screen 104 and a baffle 100. 96 is separated from the gas generator suction nozzle 98. As will be described below, the propellant pellet 90 may be described as a "lead free" casing propellant. By the way, the propulsion grain 90 is formed in the cylindrical shape with the single hole extended through the center part. Other shaped propellant pellets may be suitable and this type depends at least in part on the particular propellant system used.

Single (or multiple) gas generator suction nozzles 98 (eg, single nozzle 98 has a diameter of about 0.516 inch (1.32 cm)) on the end 96 of this gas generator housing 86 And is provided in a direction opposite to the sealing disc 70. The gas generator housing 86 also includes a plurality of circumferentially spaced discharge or discharge nozzles 200 located on the sidewalls of the housing 86. (Eg, the “rows” of the four nozzles each have a diameter of about 0.221 inches (0.561 cm)). Operation may be enhanced by a position closer to the outlet, but the axial position of this nozzle 200 (It may be located at the center of the housing 86.) It may also be desirable to change the number of furnaces 200. With this shape, with the discharge nozzle 200 on the side wall of the gas generator housing 86 and the suction nozzle 98 on the end 96 of the housing 86, the propellant granules 90 are pressurized medium 36 during combustion. Is introduced into the gas generator housing 86 through the suction nozzle 98 and the mixed gas from the housing 86 flows out of the housing 86 through the discharge nozzle 200. In particular, the flow of the pressurized medium 36 by the sidewalls of the gas generator housing 86 provides a pressure differential that introduces the pressurized medium 36 into the housing 86 through the suction nozzle 98. This significantly improves the performance of the inflator 30 when at least any manner of propulsion gas is produced, as described in detail below.

Gas generator 82 includes an ignition assembly 114 for igniting propulsion pellets 90 at a suitable time. The ignition assembly 114 is at least partially located in the gas generator housing 86 between the projectile 50 and the propulsion kernel 90, and includes an actuating piston 124 and at least one collision primer 120. And an ignition or booster material 144 suitable for the actuator. In particular, the actuation guide 140 at least partially functions to engage the end of the orifice sleeve 74 and the inner wall of the gas generator housing 86 to receive at least some of them and to guide the actuation piston 124 located therein. To do it. Primer holder 116 houses a number of conventional impingement primers 120 that engage one end of actuation guide 140 and are located near proximal ignition or booster material 144. Ignition or booster primer 144 is typically held adjacent to primer 120 by filling cup 148. An example of a suitable ignition or booster material 144 is an RDX aluminum booster material having a composition of 89% RDX and 11% aluminum powder added with 0.5% hydroxy propyl cellulose. Retainer 108 and baffle 112 are positioned between primer holder 116 and propulsion sleep 94. When the gas generator housing 86 is attached to the orifice sleeve 74 by bending instead of welding, the gas generator housing 86 tends to stretch during operation. Thus, for example, a corrugated spring washer (not shown) may be installed between the retainer 108 and the baffle 112 to maintain tight interaction of the elements described above.

The actuation piston 124 is slidably positioned in the actuation guide 140 and includes a continuous rim protruding member 128 aligned almost in line with the primer 120. As can be appreciated, a plurality of protrusions (not shown) can replace the continuous rim protrusion 128. A countersunk washer 136 is positioned therebetween, which washes the actuation guide 140 and a part of the actuation piston 124 to maintain the position of the actuation piston 124 away from the primer 120 (spacer ( 126)). Thus, the inadvertent engagement of the actuating piston 124 with the primer 120 is reduced. However, after the projectile 50 passes through the sealing disk 70, the energy transmitted by the projectile 50 to the actuating piston 124 is sufficient to overcome the countersunk washer 136 so that the projecting frame 128 ) May engage the primer 120 with a force sufficient to ignite at least one of the primers 120. This results in ignition of the ignition or booster material 144 and thus in the ignition of the propulsion grains 90.

During operation of the gas generator 82, the primer 120 may corrode so that the propellant gas generated by the propulsion grains 90 may pass through the primer 120. The leakage of propellant gas in this manner can adversely affect the constant performance of the inflator 30. However, this gas preferably acts on the actuating piston 124 to move the piston 124 to a sealing position with the actuation guide 140. This provides a seal that completely limits the leakage of gas through it by the gas generator 82. Thus, the propellant gas preferably flows through the gas generator nozzle 98.

Summarizing the operation of the inflator 30, the detector 14 (FIG. 1) sends a signal to the initiator 46 to propel the projectile 50. The projectile 50 initially passes through the sealing disc 70 to open the passage between the inflator housing 34 and the air or safety bag 18. The projectile 50 continues until it strikes the actuating piston 124 which strikes at least one of the primers 120 aligned in series with the protruding rim 128 attached to the actuating piston 124. Thus, the ignition or booster material 144 that ignites the propulsion pellets 90 is ignited. While the propellant granules 90 burn in the housing 86, the pressurized medium 36 passes through the suction nozzle 98 located at the end 96 of the gas generator housing 86 from the inflator housing 34. Flows into the generator housing 86. This is due to the flow of the pressurized medium 36 by the side walls of the gas generator housing 86 forming a pressure difference. This inflow of the pressurized medium 36 promotes mixing of the propellant gas and the pressurized medium 36 in the gas generator housing 86, which, as will be explained in more detail below, is a propellant gas containing a large amount of carbon monoxide and hydrogen. It is particularly preferable when oxygen is included in the pressurized medium 36 in order to react. Nevertheless, gas is discharged from the gas generator housing 86 through the discharge nozzle 200 of the side wall of the housing. As such, the flow towards the airbag or safety bag 18 is preferably increased by mixing the combustion products from the pressurizing medium 36 and the gas generator housing 86 (see FIG. 1).

As mentioned above, synthetic expander 30 utilizes a casing propellant in the form of propellant pellets 90 and utilizes a mixture of at least one inert gas and oxygen for pressurized medium 36. The casing propellant used here is a hot fuel propellant, such as a single, double or triple base propellant, and a nitramine propellant, such as a LOVA or HELOVA propellant. In particular, conventional shell-type propellants are fuel in that they range from about 2500K to about 3800K and have a combustion temperature that is typically above 300K, and these propellants produce significant amounts of CO and H ₂ without excess oxygen. The excess fuel from these propellants requires 5 to 25 mole percent, sometimes 15 to 40 mole percent, of additional oxygen of the stored gas to achieve equilibrium reactions for CO ₂ and H ₂ O.

“Typical” casing propellants that can be used for the propulsion pellets 90 of the synthetic inflator 30 include HPC-96, dual base, lead free propellant. Lead-free propellants are based on mass, 76.6% nitrocellulose, about 13.25% nitrogen, about 20.0% nitroglycerin, about 0.6% ethyl centralite, about 1.5% barium nitrate, and about 0.9% It has a composition of potassium nitrate and about 0.4% graphite. HPC-96 is available from Hercules, Walmington, Delaware. This particular bi-base propellant contains nitrocellulose as the main component, providing desirable stabilization but cannot meet the long-term industry's criteria for long-term thermal safety.

LOVA propellants (low fragility ammunition) and HELOVA propellants (high energy vulnerable ammunition) are other "traditional" casing propellants. It is based on weight ratio of about 76.0% hexahydrotrinitrotriazine (RDX), about 12.0% cellulose acetate butyrate, about 4.0% nitrocellulose (12.6% nitrogen), about 7.60% Propellant grains 90, such as acetyl triethyl citrate, and an M39 lova propellant having a composition of about 0.4% ethyl centrallite. M39 Nova propellants are available from Navar Surface Warfare Center in Indian Head, Maryland, United States, and Bofors in Europe (Sweden). 30 mole percent H ₂ can be produced. LOVA and HELOVA propellants are preferred over existing dual basic propulsion systems because they currently pass US automotive safety standards, while dual basic propellants are different. However, relatively high operating pressures are required for stable combustion of LOVA and HELOVA propellants. Despite the features of the HPC-96 and LOVA promoters, they only illustrate at least some of the principles and features of the present invention.

When oxygen is used as part of the pressurized medium 36 and the casing propellant is used in the form of propellant granules 90, for example, 20 to 20 are available from the assignee of the present application due to the performance characteristics of the casing propellant. Compared to current designs using 30 grams of FN1061-10, the amount of propellant required for gas generator 82 can be reduced. (FN1061-10 is about 7.93% polyvinyl chloride based on weight percent, 7.17% dioctyl adipate, 0.05% carbon black, 0.35% stabilizer, 8.5% sodium oxalic acid, 75% potassium percholate, and about 1% lecithin For example, in the case of a casing propellant that may be used in the form of a propulsion pellet 90, the weight range of the total pellet (when applied next to the passenger) is about 10 grams to 12 grams, Preferably about 15 grams or less The. In this case, it is preferable to use a pressurized medium 36 in which about 10% to 30% is oxygen based on moles. In particular, when about 169 grams of pressurized mat 36 containing about 15% oxygen in moles are used, the total weight of the propellant granules 90 may be about 10.4 grams. If applied to the driver's side, the desired or required amount of propulsion granules may be about 5 grams and, if applied to the side inflator, about 1.5 grams.

This reduction in the amount of casing propellant compared to the FN 1061-10 propellant described above can be expressed as the weight ratio between the total weight of the pressurized medium 36 and the propellant pellets 90. With regard to FN 1061-10, the assignee of the present application utilizes a ratio of about 7.04 between the weight of argon (ie, the storage gas corresponding to the pressurized medium 36 associated with the present invention) and the weight of FN 1061-10. With regard to the use of shell-type propellants, the range of the ratio between the weight of the pressurized medium 36 and the weight of the propellant grains 90 is about 10-20 to obtain an inflator with the same output and weight and size as an inflator with FN1061-10. More preferably 14 to 18, most preferably about 15 or more. As can be appreciated, this ratio can be increased by using a high temperature propellant that requires a small amount of propellant. In this regard, since the exhaust gas of the shelled propellant is almost free of hot particulate matter, the inflator of the present invention can produce exhaust gas at a higher temperature than particulate-covered expanders such as prior art expanders. This increase in temperature makes the inflator compact and lightweight because hot gases are relatively expensive. In addition to this, when the casing propellant is used, the size and weight of the inflator structure can be reduced. For example, using a ratio of 7.04 for the inflator's shell propellant yields the same power as the FN 1061-10 with this ratio, while an expander with a casing propellant may use FN 1061-10. The size and weight can be reduced by 50% compared to the inflator used. The same ratio of 7.04 can be used for the driver-side and side inflators as described above.

Compared to the FN 1061-10 propellant component described above, the aforementioned reduction in weight of the shell-type propellant is equivalent to the total gram moles of total gas emissions (i.e., the combination of the propellant gas and the pressurized medium 36) and the total of the propellant pellets 90. It can be expressed as the ratio between weights. Regarding the FN 1061-10 propellant, the assignee of the present application utilizes a ratio of 0.192 gram moles or grams between the moles of exhaust gas and the weight of the propellant. Conversely, in the case of an inflator casing propellant of the same output, weight and size, the range of the ratio between the moles of off-gas and the total weight of the propellant pellets 90 ranges from about 0.35 grams mole per gram of propellant to about grams of propellant. 0.5 gram mole, more preferably about 0.4 gram mole to about 0.5 gram mole per gram of propellant, and most preferably about 0.5 gram mole per gram of propellant. As mentioned earlier, in the case of a synthetic inflator using a casing propellant and using a ratio of 0.192 gram moles or grams of propellant, the output of the inflator is the same as the synthetic inflator using FN1061-10, but the weight of the casing propellant inflator And the size is reduced by about 50%. By using a variety of gases for the pressurized medium 36 it is possible to use at least one type of casing propellant for the reverse granules 90. Typically, the pressurized medium 36 is composed of at least one inert gas or oxygen. Suitable inert gases include arcon, nitrogen, helium, and neon, of which arcon is preferred. The oxygen portion of the pressurized medium performs various functions. Initially, the reaction of the gaseous combustion product and the oxygen of the shelled propellant of the propellant pellet 90 provides a heat source that contributes to the expansion of the inert gas. This serves to at least reduce the amount of propellant required for the gas generator 82. In addition, the reaction of oxygen with the propellant combustion product serves to reduce the existing toxicity level of the propellant gas to an acceptable level. For example, preferably oxygen converts some existing carbon monoxide to carbon dioxide (eg, converts at least 85% of CO to CO ₂ ) and converts existing hydrogen into water vapor (eg, H _Converts at least 80% of ₂ to H ₂ O, and some unburned hydrocarbons are similarly removed (eg, at least 75% of the hydrocarbons are removed). Thus, the gas generator 82 described above The performance is significantly improved. That is, the medium 36 containing oxygen is introduced into the gas generator housing 86 through the suction nozzle 98 on the end 96 of the housing 86 by the pressure difference. This pressure difference is formed by the flow of the pressurizing medium 36 by the side wall of the gas generator housing 86 with the discharge nozzle 200. Thus, the medium 36 and the CO are mixed, and hydrogen-rich combustion products are formed in the gas product, which greatly improves the overall combustion efficiency of the gas product, and the combustion product of the oxygen-rich medium 36 and the gas product is formed. There is a burning rate of the mixed and propulsion kernels 90. At this time, the gas is introduced from the discharge nozzle 200 on the side wall of the housing 36. This type of gas generator housing 86 improves the performance of the inflator 30 (e.g., by quickly and efficiently propelling the mixing of oxygen and propellant gas).

The amount of at least one inert gas based on moles is about 70% to 90% and the amount of oxygen is 10% to 30%. However, as mentioned above, the pressurized medium may comprise 70% to 92% inert fluid and about 8% to 30% oxygen on a molar basis. Usually, it is desirable to use an amount of oxygen that exceeds that based on theoretical conversion. However, it is desirable to contain about 20% or less of oxygen in the off-gas (ie, the combination of the propellant and the pressurized medium).

The inflator 30 can be assembled in the following manner. Initially, the gas generator 82 is assembled according to the following steps. 1) Insert baffle 100 and screen 104 into gas generator housing 86 adjacent discharge end 96. 2) Insert the propulsion sleeve 94 into the gas generator housing 86. 3) Propulsion pellets 90 are provided in the propulsion sleeve 94. 4) Insert the baffle 112 and retainer 108 into the gas generator housing 86 adjacent to the end of the propulsion sleeve 94 opposite the discharge end 96 of the gas generator. 5) Insert primer holder 116 with ignition or booster material 144 and filling cup 148 into gas generator housing 86. 6) Insert the operation guide 140, the dishwasher 136 and the operation piston 124 into the gas generator housing 86. Next, the gas generator housing 86 is welded to the orifice sleeve 74 and the projectile 50 and the initiator 46 are positioned in the diffuser 38 and then the diffuser 66 is welded to the boss 66 and the boss 66. The various members are connected to each other by welding the sealing disc 70 between the orifice sleeve 74 and the boss 66 to the inflator housing 34. By this structural integrity, the pressurizing medium 36 can be introduced into the inflator housing 34. In this regard, in the case of several gases, argon and oxygen can be introduced independently into the inflator housing 34 via an end plug 42 welded to the end of the inflator housing 34 (eg, argon initially). Or other inert gas and then oxygen or vice versa) or in a premixed state.

The following example helps explain the various properties associated with the use of bullet propellants in synthetic expanders.

View 1

The aforementioned HPC-96 was used to form a propulsion pellet 90 having a total weight of 18 grams. Each propulsion granule 90 is of the shape shown in FIG. 2 and has a length or thickness of about 0.52 inches (1.32 cm), an outer diameter of about 0.29 inches (0.74 cm), and about 0.105 inches (0.267 cm). Web thickness (1/2 of the difference between the inner and outer diameters of the propulsion pellets 90). The HPC-96 propellant also has a momentum of 363,493 ft-lbs / lb (50.25x10 ³ kg-m / kg), 1,062 calories / gram of explosion heat, and a temperature of 3490K (T _v ) when ignited in air. ), 26.7 grams / mole of gas, 1.2196 special heat rate, and 1.65 grams / cubic centimeter (g / cm ³ ) of solid density. Based on the theoretical calculation of the normal component, assuming a combustion at the firing pressure expanded to atmospheric pressure, the molar percentage of the gas component is about 26.5% carbon monoxide, about 19.1% water, about 26.2% carbon dioxide, and about 13.7% It consists of nitrogen, about 14.2% water bath and other gases.

When the propulsion grain 90 of the HPC-96 undergoes an industrial safety Taliani thermal safety test at a temperature of 120 ° C., the grain 90 discolors in about 40 minutes and ignites in about 5 hours. This reduces the desire to use the HPC-90 propellant for the propulsion granules 90, because current industry standards indicate that when a proliferative propulsion propellant is exposed to temperatures of 107 ° C. for 400 hours, it hardly degrades. Because it requires the propellant to ignite when exposed to autoignition temperatures. However, HPC-90 propellants are included here because they do not explain any of the principles of the present invention.

With respect to the HPC-96 propulsion pellet 90, about 169 grams of pressurized medium 36 is supplied to the inflator housing 34, which is pressurized with about 5% oxygen and about 95% nitrogen on a molar basis. Consists of. The inflator 30 has four orifice holes 78 each about 0.226 inches (0.57 cm) in diameter on the orifice sleeve 74, and the gas generator nozzle 98 has a diameter of about 0.469 inches (1.19 cm). Have There is no discharge nozzle 200 provided on the side wall of the gas generator housing 86. As such, the pressurized medium 36 flows into the gas generator 82 during operation and is discharged through the nozzle 98.

The pressure change in the inflator housing 34 during operation of the inflator 30 is similar to that shown in FIG. 3 and the pressure in the 100 liter tank in fluid communication with the inflator 30 is shown in FIG. Similar to this represents pressure build-up in the safety bag or airbag 18. Exhaust gas from inflator 30 contains about 1.2% carbon monoxide, about 1.5% carbon dioxide, about 2% or more hydrogen, and about 60 ppm NO _X on a molar basis. Thus, the use of oxygen and argon in the aforementioned ratios significantly reduces the amount of carbon monoxide and hydrogen compared to the theoretical gas emissions of the HPC-96 propellant mentioned above. In this example, no radial holes were used and a single gas generator outlet was used.

View 2

Although the procedure in Example 1 was repeated, 10.4 grams of HPC-96 propellant was used for the propellant pellets (90) and 164.4 grams of pressurized medium containing about 15% oxygen and about 85% argon on a molar basis. (36) was used. The performance curves of the inflator 30, when actuated by such propulsion granules 90, are shown in FIGS. 3 and 4 and the inflator 30 is formed in the manner of FIG. 1. In addition, exhaust gas from expander 30 contains about 2.4% carbon monoxide, about 1000 ppm carbon monoxide, about 70 ppm NO _X , about 38 ppm NO ₂ , and about Oppm hydrogen. Thus, while the amount of oxygen increases from 5% to 15%, it is significantly reduced in the amount of carbon monoxide without a significant increase in NO and NO ₂ . This also makes it possible to use quite a small amount of propellant.

View 3

The procedure of Example 1 was repeated twice using 169.0 grams of pressurized medium 36 consisting of about 15% oxygen and about 85% argon and 10.4 grams of HPC 96 on a molar basis. The performance curve of inflator 30 is similar to that shown in FIGS. 3 and 4 and inflator 30 is formed in the manner of Example 1. In addition, the exhaust gas from the expander 30 contains 1000 ppm and 800 ppm carbon monoxide, about 1.0% and 1.2% carbon dioxide, about 60 ppm and 50 ppm NO _X , and about 23 ppm and 20 ppm NO ₂ , respectively. Thus, a 15% increase in the amount of oxygen and a decrease in the amount of HPC 96 reduce the amount of carbon monoxide without significantly affecting NO and NO ₂ . In addition, increasing the amount of oxygen makes it possible to use less amount of propellant.

As mentioned above, two existing "traditional" shell-type propellants (traditional dual-base casing-type propellants and fragile nitiramine (LOVA) propellants) were initially considered for this application. By means of these conventional double-base casings, the safety device performs the expected function but does not pass the safety standard when stored for a long time (eg 400 hours at 107 ° C.). The LOVA stripped propellant is determined to be unsatisfactory unless the propellant burns at very high pressures, which adds weight, cost and design complexity. Typically, it is desirable to use a pressure of up to 4,000 psi for the inflator. Under these conditions, because the existing propellants are not satisfactory in the present application, a new type of propellant has been developed. This type of propellant is a combination of a propellant with good ignition and combustion at low ballistic characteristics of the double base propellant and a storage characteristic of the nitramine LOVA propulsion agent (which performs well after storage at 107 ° C. for 400 hours). This kind of propellant is referred to as synthetic propellant.

Unlike the nitrocellulose-based propellant of the HPC-96 thermally stabilized shell propellant, it contains a second explosive when used in the form of a propulsion kernel 90, ie nitramine (RDX) in the case of LOVA propellant. Other suitable explosives that may be used in the form of propellant granules (90) include HMX (cyclotetramethylene tetranitramine), as well as other types of PETN (pentaerythritol tetranitrate) and TAGN (triaminoguanidine nitrate). Contains nitramine. Table 1 below provides certain combustion characteristics for the second explosives of RDX, HMX and PETN.

Table 1

Typically, in order to achieve the desired combination of desired ballistic properties and long term thermal stability (e.g., to achieve a ballistic characteristic of a double base propellant and a long term numerical characteristic or long term thermal stability of a LOVA propellant), the second explosive is propelled. It can be combined with the bonding system in the form of granules 90 (as mentioned earlier as "synthetic propellant"). The "bonding system" used herein is useful for modifying the physical, chemical, and ballistic properties of the propellant. Reference is made to at least one composition added to the propellant. Useful bonding systems include systems incorporating propellant additives selected from the group consisting of adhesives, plasticizers, stabilizers, opaque agents and mixtures thereof.

The synthetic propellant for the propulsion granules 90 of the composite expander 30 exhibits good ballistic properties (i.e. burn rate and combustion year at relatively low operating pressures) and acceptable acceptable long-term safety (e.g., long term thermal safety). An industrial test to impose a statistically sufficient number of specimens to withstand (not ignite) exposure to a temperature of 107 ° C. for 400 hours. Other tests have unacceptable performance (typically formed by the user). Or withstand) without exposure to temperatures of 100 ° C. In particular, the propellant granules 90 formed of synthetic polymers have a rate ranging from about 0.1 inch (0.25 cm) (0.25 cm / s) to about 1 inch (2.5 cm) (2.5 cm / s) per second. It is combusted at a combustion temperature ranging from about 3,800K to about 3,800 psi and an operating pressure of about 4,00 psi (27.6 Mpa) (pressure in gas generator housing 84). In particular, the propellant pellets 90 formed of synthetic propellant are combusted at a combustion temperature in the range of 2000K to 3800K and an operating temperature of about 4,00 psi (27.6 Mpa) at a ratio in the range of about 0.76 cm / s to about 1.26 cm / s.

Typically, the type of synthetic propellant comprises about 50 wt% to 90 wt% of the second explosive and about 10 wt% to 50 wt% of the bonding system. In particular, this type of propellant comprises about 60 wt% to 80 wt% of the second explosive and about 20 wt% to 40 wt% of the bonding system. Preferably, the type of propellant comprises about 20 wt% to 30 wt% bonding system of the second explosive having a property of about 70 wt% to 80 wt%. Other additives and unavoidable impurities may also be present in the propellant component in small amounts (ie, in amounts less than about 5 wt% of the component).

Typically, the resinous binder is part of a bonding system for the synthetic propellant type for the propulsion pellets 90. Almost any binder can be used that is soluble in common solvents (ie, acetone, low alcohol, etc.). However, such binders are preferably active or potent compounds. That is, the binder is more preferably easy to burn at the desired combustion temperatures and operating pressures described above. Moreover, when using a binder in combination with a plasticizer, it is preferable to match a binder with a plasticizer. Conventional binders in a suitable manner used in the propellant component include, without limitation, CA (cellulose acetate), CAB (cellulose acetate butyrate), EC (ethyl cellulose) and PVA (polyvinyl acetate). Other types of binders suitable for use in at least one of the properties associated with the present invention include cap (cellulose acetate propionate), azide polymers, polybutadiene, polybutadiene hydrides, polyurethanes and mixtures thereof have. The azide polymers mentioned are among the group comprising GA (glycidazide) units, BAMO (3,3bis (azidementyl) oxetane) units, and AMMO (azidementyl methyloxetane) units Homopolymers or interpolymers containing the selected units. In addition, GAP (Strong Glycid Azide Polymer) can be used as a bonding component and burns more actively than CA. Thus, it is preferable to use only GAP as a binder with a 2nd explosive. However, due to the significant cost difference between GAP and CA, the synthetic propellant format may include both GAP and CA subtractive components.

Plasticizers may also be used as part of a suitable system for the synthetic polymer format for the propulsion pellets 90. As noted, the plasticizer must be compatible with the binder. It is also desirable to use protruding bonding systems. In addition, in the case of at least any second explosive (eg, nitramine), it is preferable to use a strong plasticizer, such as a plasticizer which is stably combustible within the aforementioned operating temperatures and pressures. Useful powerful plasticizers include TEGDN (triethyleneglycol dinitrate) and glycid azide plasticizers such as TMETN (trimethyloletan trinitrate), BTTN (butanetriol trinitrate), NG (nitroglycerin) and Other composites and plasticizers selected from the group aqueous with nitrate ester plasticizers such as BDNPA / F (bis (2,2 dinitropropyl) acetal / formal). Other plasticizers suitable for at least one or more properties according to the present invention include ATEC (acetyl triethyl citrate).

In addition, stabilizers may be included in the bonding system for the synthetic polymer format for the propulsion pellets 90. For example, any binder or plasticizer, such as the nitrate ester plasticizer mentioned above, may be analyzed and influence the combustion of the propellant grains 90 according to exposure to any temperature. The nitrate ester plasticizer is thermally analyzed as the viscosity at which ignition occurs upon exposure to heat. Thus, in order to maintain stability (e.g., to reduce the possibility of precombustion of the propellant), the binder and the plasticizer are thermally Stabilizers may be included in the type of synthetic propellant that is analyzed and reacted to enhance the long-term stability of the synthetic propellant. For example, in the case of nitrate ester plasticizers, stabilizers useful in the form of propellants include active materials such as nitrate acceptors. Suitable esters include ethyl centrallite (simdiethyldiphenylurea), DPA (diphenylamine) and resorcinol.

The type of synthetic polymer that has the desired ballistic properties and is provided with sufficient indication of suitable long-term safety is a combination of a bonding system comprising nitramine second explosive RDX (hexahydrotrinitrotriazine) and binder CA (cellulose acetate). And the plasticizer TMETN (trimethyloletan trinitrate) and the stabilizer EC (ethyl central light). Typically, the type of such synthetic propellant may comprise at least about 70 wt% RDX, about 5 wt% to 15 wt% CA, about 5 wt% to 15 wt% TMETN, and up to about 2 wt% EC. . Such conventional relative amounts provide the desired ballistic and long term maturation properties for synthetic propellants. However, when the propellant grains 90 protrude from this type of propellant, it is necessary to improve the relative amounts within the previously specified range.

For at least one characteristic associated with the present invention, the propellant is about 70 wt% RDX (hexahexatritritrotriazine), about 5 wt% to about 15 wt% CA (cellulose acetate), and about 5 wt% to 15 wt% GAP (glycides azide polymer), and ATEC (acetyl triethyl citrate). If the conjugation system comprises a mixture of binder, plasticizer and stabilizer, the ratio of each agent of the mixture is preferably in the range of about 5 to 30%, 0 to about 20 wt% and 0 to 5 wt%.

Other types of synthetic propellants that have the desired ballistic properties and provide adequate long-term safety indications include a nitramine second explosive RDX with a bonding system comprising binder CA and GAP (glycides azide polymer), Suitable stabilizers (eg, GAP stabilizers, TMETN, ATEC and mixtures thereof). Typically, the type of such synthetic propellant is at least about 70 wt% and typically about 70 wt% to about 80 wt% RDX, about 5 wt% to 15 wt% CA, about 5 wt% to 15 wt% GAP, and about 5 wt% % To 15wt% stabilizer may be included. This general relative amount provides the desired ballistic and long term maturation properties for the synthetic propellant. However, in the case where the propulsion grains 90 are formed by protruding from this type, the correction of the relative amount is necessary within the designated range.

In the case of the synthetic propellants described herein, as in the case of the dual base and LOVA propellants mentioned above, significant amounts of carbon monoxide and hydrogen are produced during combustion (eg, 35% CO and 19% H ₂ O). . Again the formation of carbon monoxide and hydrogen gas through combustion of the expander propellant is typically unacceptable for automatic expansion stabilizers. However, when a synthetic propellant of this type is used in the synthetic expander 30 as mentioned above, the pressurized medium 36 contains oxygen and carbon monoxide and in subsequent subsequent reactions to carbon monoxide and water vapor which are also harmful during combustion. Most of the hydrogen (eg 95%) is converted. The use of stored oxygen gas is particularly desirable because it obviates the need to include an oxygen source (eg, potassium percholate) in the form of synthetic propellant. In addition, high exothermic reactions between the combustion propulsion gases produced by the stored oxygen are desirable because these reactions enhance the heating value of the propellant to minimize the amount of propellant required to inflate the airbag and safety bag.

The synthetic propellant can be used in the amounts mentioned above with respect to the casing propellant when formed into the composite pellets 90 and incorporated into the synthetic inflator 30. In particular, the amount of the propellant contains the fine particles described above with respect to the relative amounts of the propellant grains 90 and the pressurized medium 36. Moreover, the relative amounts of oxygen and inert gas for the pressurized medium 36 may be used in the case of the synthetic propellants disclosed herein.

The following example helps to explain the suitable properties of the type of synthetic propellant comprising the second explosive and the conjugation system. As mentioned above, all references to "wt%" refer to weight ratios.

Example 4

At least about 70 wt% hexahydrotrinitrotriazine (RDX), about 5 wt% to 15 wt% CA (cellulose acetate), about 5 wt% to 15 wt% TMETN (trimethyloletal trinitrate) and up to about 2 wt% Synthetic propellant components comprising ethyl centrallite were prepared to form cylindrical pellets with an average density of about 1.7132 g / cc. Ten grams of test specimens were installed in the weight chamber bomb chamber and ignited into the tank. The test specimen has a combustion temperature of about 2578K and exhibits acceptable ballistic properties (ie, a burn rate of 1.18 cm / s at 400 psi (27.6 Mpa)). Typically, the performance curve is similar to that shown in FIGS. 3 and 4. The resulting gas contains about 36% carbon monoxide, about 24% nitrogen, about 19% hydrogen, about 16% water vapor and about 5% carbon dioxide. Long term thermal safety of the composite was evaluated and it was determined to be acceptable. For example, the propellant was exposed to a temperature of 107 ° C. for 400 hours and did not ignite, and the propellant did not ignite when exposed to a temperature of 107 ° C. for 400 hours when accommodated in a synthetic expander, and then the In operation, its performance was hardly affected by heat treatment.)

Example 5

Propellant comprising at least about 70 wt% RDX (hexahydrotrinitrotriazine), about 5 wt% to 15 wt% cellulose acetate, and about 5 wt% to about 15 wt% GAP (glycides azide polymer) The ingredients were prepared and formed into cylindrical pellets with an average density of about 1.6857 g / cc. Ten grams of test specimens were installed in the spring chamber of the heavy wall and ignited into the tank. The test sample had a combustion temperature of about 2,357K and exhibited acceptable ballistic properties (ie, a burn rate of 1.18 cm / s at 4000 psi (27.6 Mpa)). Typically, the performance curve was nearly similar to that shown in FIG. 3 and FIG. The resulting exhaust gas contains about 37% carbon monoxide, about 25% hydrogen, about 25% nitrogen, about 10% water vapor and about 3% carbon monoxide. The long term thermal stability of the composite was evaluated and determined to be acceptable (e.g., the propellant was exposed to a temperature of 107 ° C. for about 400 hours and did not ignite, and the propellant was 107 for 400 hours when accommodated in the synthetic expander). It was not ignited when exposed to a temperature of < RTI ID = 0.0 >

Other features of the propellant that may be used in at least one of the properties associated with the present invention include hexogen (RDX) in the range of about 1 to 99, and octogen (HMX) in the range of about 1 to 99. And a binder in which the sum of hexagen and octogen is mixed in an amount of 100 parts by weight. The binder is in the range of 5 to 50 parts by weight. Preferably, the aforementioned propellant comprises hexogen (RDX) in the range of 80 to 95 parts by weight and octogen (HMX) in the range of 5 to 20.

The aforementioned propellants can be used in synthetic expanders such as those described herein. Again, the composite inflator includes a pressurized gas chamber containing a pressurized medium, a gas generating chamber containing a propellant, an igniter assembly and a bursting disc. The pressurized medium consists of an inert fluid and oxygen. The propellant, for example, is combusted to produce gaseous products (eg, carbon monoxide and hydrogen) that are ignited by the igniter assembly and react with oxygen when a predetermined amount of deceleration occurs. Carbon monoxide and hydrogen react with oxygen in the pressurized gas to produce carbon monoxide and water vapor while simultaneously increasing the pressure in the gas generator chamber. Thus, the bursting disc is opened to supply carbon dioxide, water vapor and an inert gas to the airbag and safety bag 18 (FIG. 1 FIG. 1). This inflates the airbag or safety bag 18.

The aforementioned propellant gases include hexogen (RDX), octogen (HMX), and binders. RDX and HMX ranges from 1 to 99 parts by weight, respectively. Preferably, the content of RDX and HMX ranges from 80 to 95 and 5 to 20 by weight, respectively. The binder is a mixture of hexogen and octogen in parts by weight of 100 and ranges from 5 to 50 parts by weight.

Conventional binders suitable for use in the aforementioned propellants include polyurethane (PU), cellulose derivatives such as ethyl cellulose (EC), cellulose acetate butyrate (CAB), cellulose acetate propinate (CAP), hydroxy terminated polybutadiene Polybutadiene such as (HTPB), azide polymers such as glycid nitrate polymer (GAP), and 3-nitratemethyl-3-methyl-oxetane polymer (polynimo). Of these, cellulose acetate butyrate (CAB) or glycid azide polymer (GAP) is preferred.

The aforementioned propellant comprises an additive selected from the group consisting of plasticizers, stabilizers and mixtures thereof. Plasticizers include TMETN (trimethyl oletan trinitrate), BTTN (butanriol trinitrate), TEGDN (triethylene glycol dinitrate), glycid azide, NG (nitroglycerin), BDNPA / F ( Bis (2,2-dinitropropyl) acetal / formal) and ATEC (acetyl triethyl citrate).

Stabilizers including ethyl centralide, diphenyl amine, resorcinol, alkadit 11, amyl alcohol, urea, petroleum jelly can be used as the propellants mentioned above.

Plasticizers may be added to the total weight of 100 RDX, HMX, and binder in a weight ranging from 1 to 30. The aforementioned propellants may be formed in powder, granular and granular form, of which granules are most preferred.

Example 6

The following materials were mixed with each other to form a tablet and then filled into a composite inflator comprising a pressurized gas chamber, a gas generating chamber, an igniter assembly, and a bursting disc. The synthetic expander was activated, resulting in no smoke of KCL.

Note: The content ratio of the binder (CAB and GAP) to 100 parts by weight of RDX and HMX is about 16 parts by weight.

Example 7

The following materials were mixed together and formed into tablets and then filled into a synthetic expander having the same structure as Example 6. As a result, no smoke was produced.

Note: The content of binder (CAB and GAP) relative to 100 parts by weight of RDX and HMX is about 32 parts by weight.

Example 8

The following materials were mixed together and formed into tablets and then filled into a synthetic expander having the same structure as Example 6. As a result, no smoke was produced.

Note: The content of binder (CAB and GAP) relative to 100 parts by weight of RDX and HMX is about 32 parts by weight.

View 9

The following materials were mixed together and formed into tablets and then filled into a synthetic expander having the same structure as Example 6. As a result, no smoke was produced.

Note: The content of binder (CAB and GAP) relative to 100 parts by weight of RDX and HMX is about 32 parts by weight.

Example 10

The following materials were mixed together and formed into tablets and then filled into a synthetic expander having the same structure as Example 6. As a result, no smoke was produced.

Note: The content of binder (CAB and GAP) relative to 100 parts by weight of RDX and HMX is about 32 parts by weight.

Example 11

The following materials were mixed together and formed into tablets and then filled into a synthetic expander having the same structure as Example 6. As a result, no smoke was produced

Note: The content of binder (CAB and GAP) relative to 100 parts by weight of RDX and HMX is about 32 parts by weight.

Example 12

The following materials were mixed together and formed into tablets and then filled into a synthetic expander having the same structure as Example 6. As a result, no smoke was produced.

Note: The content of binder (CAB and GAP) relative to 100 parts by weight of RDX and HMX is about 32 parts by weight.

Example 13

The following materials were mixed together and formed into tablets and then filled into a synthetic expander having the same structure as Example 6. As a result, no smoke was produced.

Note: The content of binder (CAB and GAP) relative to 100 parts by weight of RDX and HMX is about 32 parts by weight.

Example 14

The following materials were mixed together and formed into tablets and then filled into a synthetic expander having the same structure as Example 6. As a result, no smoke was produced.

Note: The content of binder (CAB and GAP) relative to 100 parts by weight of RDX and HMX is about 32 parts by weight.

As mentioned above, synthetic expanders that do not produce KCl small in operation can be prepared by using propellants including hexogen, octogen, and binders.

Another embodiment of a composite inflator that can be used in the inflatable safety of FIG. 1 is shown in FIGS. Referring to FIG. 5, the composite inflator 202 includes a conventional cylindrical gas generator 208 and a conventional cylindrical storage gas housing 204. The storage gas housing 204 is located concentrically around the gas generator 208 and connected to the gas generator 208 in an appropriate manner. Typically, the storage gas housing 204 (third chamber) contains a suitable pressurized medium, and the gas generator 208 contains a grain 258 of a suitable propellant. The main advantage of the inflator 202 is that the fluid pressure is applied directly to the opening of the second sealing disk 209 so that the design is such that the second sealing disk 290 or the main sealing disk (inflator 202 and the airbag or It isolates the flow between safety bags 18 (FIG. 1), which affects the rapid pressurization of the area nearby. Another advantage of the design of the inflator 202 is that it provides or allows sufficient "mixing" of the propellant gas produced upon ignition and combustion of the propellant pellets 258 by the pressurized medium. Thus, the inflator 202 is intended for use with the aforementioned composites of casings or synthetic propellants with a multicomponent pressurized medium (eg, one component is oxygen and the other component is at least one inert gas). Especially suitable. That is, the design of the inflator 202 may be such that the gas produced by ignition of the propellant pellets 258 by the pressurized medium (eg, to enhance the operation of the expandable safety device 10 (see FIG. 1)). As described hereinafter, it provides or allows for the efficient combustion of propellant gases) or gases produced by the combination of ignition or booster materials 240. This secondary combustion further enhances the rapid pressurization capacity of the inflator 202 to initiate flow towards the airbag or safety bag 18.

The gas generator 208 includes, in the illustrated embodiment, a gas generator housing 212 formed as the first housing 216 and a second housing 218 arranged axially and connected to each other. One end of the first housing 216 is preferably attached to the initiator adapter 224 to achieve a hermetic sealing. The initiator adapter 224 has a suitable initiator 228 (e.g., an electrically actuated squib or other suitable flame igniter) (e.g., by welding at the welding point). This initiator is used for the purpose of igniting the propellant pellets 258 and can be fitted within the O-ring 232 to form a suitable seal. In order to isolate the initiator 228 from the pressurized medium in the gas generator 208, the first sealing disk (second sealing disk) is formed at the end of the first housing 216 to achieve the desired hermetic sealing through the welding point 248. And between the ends of the initiator adapter 224.

The first housing 216 of the gas generator housing 212 defines a first chamber 254 arranged axially adjacent to the initiator 228. The first chamber 254 of the gas generator housing 212 contains a propulsion pellet 258 that produces a propellant gas to increase flow to the airbag or safety bag 18 upon ignition. Thus, the first chamber 254 may be characterized as a propulsion chamber or combustion chamber. In order to account for the combustion of the propellant granules 258, an appropriate ignition or booster material 240 is positioned in alignment with the initiator 228 between the initiator 228 and the propellant kernels 258. Such ignition or booster material 240 is, for example, 0.5 wt% to 5.0 wt% RDX and 89 et% RDX with 0.5 wt% to 5.0 wt% of hydroxypropylcellulose added in place of aluminum and 11 wt%. RDX or aluminum booster material with% aluminum powder. As will be described later, the reaction product of the gas resulting from ignition or ignition of the booster material 240 chemically reacts with the pressurized medium to further enhance the rapid pressurized flow start characteristics of the expander 202. Suitable booster cups 244 and the like hold ignition or booster material 240 (typically powdered or dried slurry foam) and may be properly secured to the ends of the initiator adapter 224 or the first housing 216. . In addition, the first chamber 254 may be configured from the first chamber 254 to the second chamber 254 as described below (eg, by being held between the adapter 224 and the housing 216 via the welding point 248). A screen 266 or the like may be included to filter particulate matter of a predetermined size while discharging the propellant gas into the chamber 324. The capacity of the storage gas housing 204 of the inflator 202 is set larger than that of the second chamber 324.

The first chamber 254 is typically stored by at least one supply orifice or hole 262 (two in the illustrated embodiment) so that a large amount of pressurized medium is received in the first chamber 254 in the static state. In fluid communication with the housing 204. In the embodiment shown, the supply hole (s) 262 extend radially. (Ie, it extends along a radius starting at the central longitudinal axis 220 and is arranged perpendicular to the axis 220.) The feed hole 262 to "adjust" the performance of the inflator 202's performance. The size or number of) can be selected and used.

When at least one feed hole 262 is used, any amount of flow of propellant gas generated upon ignition of the propellant pellets 258 is introduced into the storage gas housing 204. When the propellant of the aforementioned manner (e.g., casing synthetic propulsion) and the pressurized medium (e.g. a mixture of oxygen and an inert fluid (at least one gas)) are ignited, some secondary combustion, ie propellant gas Further combustion occurs in the storage gas housing 204. A portion of the propellant gas from the first chamber 254 towards the storage gas housing 204 to achieve the desired output or discharge towards the airbag or safety bag 18, ie to achieve the desired expansion rate of the airbag or safety bag 18. May spill. In particular, as described below, it is desirable to supply the propellant gas to the storage gas housing 204 at a rate that maintains a substantially constant flow from the storage gas housing 204 into the second chamber 324 for a sufficient time. Typically, one of the propellant gases generated during operation to achieve the desired result (e.g., about 40% or less of the flow rate of the propellant gas, and more generally about 30% or less into the storage gas housing 204) is achieved. Only a small amount of is needed to flow into the storage gas housing 204.

When the feed hole 262 is used, the pressure increase in the storage gas housing 204 after ignition of the propulsion pellets 358 is lower than in the design of many commercial composite expanders. That is, the significant increase in pressure associated with ignition of the propulsion grains 358 is limited to the gas generator 208. Thus, the need for "strength" of the storage gas housing 204 can be reduced. This reduces wall thickness in the case of a storage gas housing 204 or lightweight material that increases the weight of the inflator 202.

Propellant gas from the first chamber 254 toward the second chamber 324 formed by the second housing 278 of the gas generator housing 212 (known as " afterburner " as described below). Of flow (eg, at least about 50% and typically at least about 70% of the total propellant gas flow) is important. At least one late combustor nozzle or aspirator 274 (first connection hole) introduces a fluid (primarily a propulsion gas) from the first chamber 254 into the second chamber 324, thereby reducing the Provide delivery. The late combustor nozzle 274 can be fitted in contact with the shoulder 270 on the interior of the first housing 216 and prior to properly connecting the first housing 216 and the second housing 278 to each other (e.g., For example, by welding at the welding point 250).

In the illustrated embodiment, one end of the second housing 278 of the gas generator housing 212 can be fitted into a late combustor adapter 282 with at least one gas generator outlet 286. O-ring 328 may be used between the second housing 278 and the adapter 282 to provide a suitable sealing contact surface. The late combustor adapter 282 is suitably secured to the storage gas housing 204 (e.g., to achieve a hermetic seal) since the second chamber 324 accommodates a large amount of pressurized medium in a stationary state (e.g. And fixed at the welding point 312 in a manner appropriate to the boss 294 (eg, welding at the welding point 308). At the welding point 308 by positioning the second sealing disk 290 between the end of the late combustor adapter 282 and the boss 294 in order to receive the pressurized medium in the inflator 202 until the desired time. The disk is thereby restrained.

Based on the fluid shear between the first chamber 254 and the second chamber 324, the propellant gas produced by the combustion of the propellant granules 258 and the gas produced by the ignition of the ignition or booster material 240 are at least. Partially introduced into the second (late combustor) chamber 324. The rapid rise in pressure in the second chamber causes the flow of fluid from the inflator 202 into the diffuser 298 and then into the airbag or safety bag 18 (FIG. 1) when controlled in the manner described below. The second burst disk 290 is opened at an appropriate time. The diffuser 298 utilizes a plurality of diffuser holes 300 to provide relatively non-propulsive output to the airbag or safety bag 18. Diffusion screen 304 is incorporated into diffuser 298 to inhibit any particulate matter in inflator 202 or to further promote mixing and reaction of the propellant gas or pressurized medium prior to passing through air bag (safety bag) 18. May be included.

The second chamber 324 is also in fluid communication with the storage gas housing 204. In this regard, at least one and preferably a plurality of gas generator intakes 316 are provided with the storage gas housing 204 and at least one such that the pressurized medium from the storage gas housing 204 is introduced into the second chamber 324 at a suitable time. Provides fluid communication between the two chambers 324. That is, for any application the flow of this particular fluid can be controlled in terms of the direction of flow. In particular, the valve 320 may be located adjacent to at least one and preferably all gas generator inlets 316. In the stopped state, the valve 320 does not need to actually isolate the storage gas housing 204 from the second chamber 320 in this zone. In practice, preferably, a large amount of pressurized medium is suppressed in the second chamber 324 in a stationary state so that the unsealed contact surface receives this supply. The shape of the valve 320 that does not isolate the second chamber 324 from the storage gas housing 204 over the hole 316 is largely a cylindrical roll. A cantilever connection may be used between the interior of the second housing 278 and the valve 320 (eg, 0.002 inches thick, 300 rows of stainless steel). That is, the rear portion (i.e., far enough from the hole 316) can be attached to the second housing 278, which is left unattached and has a remaining front or center portion to provide actuation to the valve 320. Can be freely moved or deflected.

Based on the foregoing, the pressure throughout the storage gas housing 204 and the gas generator housing 212 at rest is approximately constant. However, the pressure across the various “chambers” of the inflator 202 after being in a dynamic state or after ignition of the propulsion granules is formed differently to achieve the desired performance. In this regard, when the propellant pellets 258 are ignited, the generated propellant gas begins to flow into at least the second chamber 324 to increase the pressure in the second chamber. When at least one feed hole 262 is integrated, a small amount of propellant gas enters the storage gas housing 204 and likewise slightly increases the pressure therein. Preferably, the pressure increases at a greater rate in the second chamber 324 than in the reservoir gas housing 204 due to the introduction of each propellant gas and each relative volume therein. This pressure difference causes the valve 320 to be pushed inside the aligned portion of the housing 212, in particular in contact with the second housing 278, thus blocking the gas generator inlet 316 so that the second chamber ( Temporarily isolate the storage gas housing 204 from 324. The cantilevered connection of the aforementioned valve 320 allows this operation. When the pressure in the second chamber 324 approaches a predetermined level, hydraulic pressure applied directly on the second sealing disk 290 opens, ruptures, or breaks the disk 290. Thus, the fluid flows from the gas generator 208 toward the diffuser 298 and then toward the airbag or safety bag 18 (FIG. 1).

As can be appreciated, valve 320 allows timely initiation of flow towards the airbag or safety bag 18 in any application. In particular, in any design, the use of the valve 320 can rapidly pressurize the second chamber 324 at a rate that opens the second sealing disk 290 at an appropriate time. If the valve 320 is not used in the inflator 202, the propellant gas flows from the second chamber 324 into the storage gas housing 204. As such, it may take a long time to increase the pressure in the second chamber 324 to a level that ruptures the second sealing disk 290. However, use of the second chamber 324 provides a compact pressurized chamber that reduces the time required to initiate flow towards the airbag or safety bag 18. As described below, in some designs, the volume of the second chamber can be made small enough, and the propellant and pressurized medium can be selected such that the valve 320 is not required for satisfactory operation. (E.g., by using combustion of gas produced by combustion of the propulsion pellets 258 or ignition and booster material 240 to affect rapid pressurization in the second chamber 324).

The valve 320 is locked in place to shut off the gas generator inlet 316 for a predetermined amount of time after the second sealing disk 290 is opened to initiate flow towards the airbag or safety bag 18. However, once a predetermined pressure difference is formed between the storage gas housing 204 and the second chamber 324, the valve 320 is moved by the force of this pressure difference to open the gas generator inlet 316. When the valve 320 is configured in the manner described above, the valve 320 is collapsed by the collapse of the valve 320 in a region radially aligned with the aperture to achieve the desired flow through the gas generator internal aperture 316. The free end of is moved radially toward the central axis 220. However, the valve 320 is fixed by the interconnection with the second housing 278. When the gas generator inlet 316 is exposed, flow begins from the reservoir gas housing 204 into the second chamber 324. The valve 320 can move from the first position to the second position. When the valve 320 is in the first position, the valve 320 is suppressed in operation. If the pressure in the reservoir gas housing 204 exceeds the pressure in the gas generator housing 212 to a predetermined degree, the valve 320 moves to the second position to allow flow. This second position is inside the yarn of the first position.

Of course, after the second sealing disk 290 is ruptured by the slight pressurization of the second chamber 324, the main function of the second chamber 324 is to push the propellant gas and the pressurized medium in advance of the discharge to the airbag or safety bag 18. To provide or allow for efficient mixing. Propellant mixtures of the aforementioned manner (e.g. casing propellants, cryogenic propellants) and pressurized media of the aforementioned manner (e.g. mixtures of oxygen and deodorizing fluids such as at least one kind of inert gas) can be used. In such a case, the mixture may further contain a propellant gas to provide the aforementioned advantages (e.g., reduced toxicity, reduced amount of propellant required for inflator 202 by further combustion and increased associated expansion performance). Burn. As such, the second chamber 324 may have additional features as a late combustor. Preferably, at least about 99% of the total combustion of the gas from the ignition of the propellant gas and the ignition or booster material, and preferably about 100% of such combustion, occurs in the expander 202. This reduces the likelihood of damage to the airbag or safety bag 18.

In order to fully understand the benefits of secondary combustion, the second chamber 324 must provide or allow mixing of the product gas and pressurized medium by length or induced turbulence, as described below. In the embodiment of FIG. 5, the closest parts of the post-combustion nozzle 274 and the gas generator inlet 316 to the gas generator outlet 26 should be at least 15 mm away from the outlet 286 when applied to the driver side. This distance may be formed in the range of about 4 mm to about 80 mm in at least one case associated with the present invention. This increase in length of the second chamber 324 also allows for receiving a sufficient amount of pressurized medium in the second chamber 324 such that the pressurized medium is at rest from the reservoir gas housing 204 to the second chamber 324. React with the propellant gas produced before the flow begins. That is, preferably, upon operation of the expander 202 to react with the propellant gas until the flow from the reservoir gas housing 204 toward the second chamber 324 is initiated by the aforementioned movement of the valve 320. A sufficient amount of pressurized medium is received in the second chamber 324.

In order to realize the benefit of the "long" second chamber 324, the gas generator inlet 316 is also spaced apart from the gas generator outlet 286 by a sufficient distance as mentioned above. Preferably, in order to facilitate further mixing of the propellant gas and the pressurized medium, most of the central or front portion of all gas generator inlets 316 (defined by their respective centerlines) should be in contact with the ends of the late combustor 273. Preferably, as shown, more rearward (ie, towards the initiator 228).

The dimensions of the design given for the inflator 202 may vary, in particular the range of preferred capacities of the inflator housing 204 depends on the application of the inflator as shown in Table 2. For example, for at least one aspect associated with the present invention, the capacity of the inflator housing 204 may range from about 150 cm ³ to about 450 cm ³ . The capacity of the first chamber 254 ranges from about 10 cm ³ to about 40 cm ³ . The capacity of the second chamber 324 ranges from about 1 cm ³ to about 50 cm ³ .

The dimensions of one embodiment are described to illustrate the principles of the invention. 1) The diameter of the storage gas housing 204 is about 59 mm. 2) The length of the reservoir gas housing 204 is about 200 mm. 3) The storage gas housing 204 is formed of a mild steel tube and has a wall thickness of about 2.5 mm. 4) The internal volume of the storage gas housing 204 (the portion that contains the storage medium and does not include the volume of the centrally arranged gas generator 208) is about 374 cm ³ (375 cc). 5) The diameter of the first housing 216 of the gas generator housing 204 is about 20 mm. 6) The length of the first chamber 254 is about 55 mm. 7) The first housing 216 is made of mild steel and has a wall thickness of about 1.5 mm. 8) The internal volume of the first chamber 254 of the gas generator housing 212 is about 11 cm ³ (11 cc). 9) The diameter of the second housing 278 of the gas generator housing 212 is about 17 mm. 10) The length of the second chamber 324 is about 90 mm. 11) The second housing 278 is made of mild steel and has a wall thickness of about 1.25 mm. 12) The internal volume of the second chamber 324 of the gas generator housing 212 is about 14 cm ³ (14 cc). 13 Six feed holes 262 are provided, each having a diameter of about 3 mm. 14) The internal bore diameter of the late combustor nozzle 274 is about 2.5 mm. 15) The gas generator outlet 286 has a diameter of about 10 mm. 16) All gas generator inlets 316 are arranged at a distance of about 76 mm from gas generator outlet 286. 17) The nozzles 274 are arranged at an interval of about 75 mm from the gas generator outlet 286. 18) The internal volume of the diffuser 289 is about 4 cm ³ (4 cc). 19) Twelve diffusion holes 300 are provided. 20) The total weight of the propagating granules is about 9 grams and has a compound of the aforementioned manner with RDX, CA and TMETN. 21) The static pressure in the expander 202 is 20.7 MPa so that there is about 140 grams of pressurized medium, about 85% of which is argon and about 15% is oxygen (in moles). 22) of the expander 202 The total weight is about 1200 grams. Where the pressurized medium comprises helium for detecting a gas leak, at least one pressurized medium in the context of the present invention is preferably from about 8% to about 30% oxygen and from about 60% to about 90% Argon and about 0.55 to about 10% helium.

Operation of the inflator 202 can be summarized primarily with reference to FIGS. 6A-6D and 7A-7D. In the stationary state, the second sealing disc 290 remains circular and the valve 320 needs to isolate the reservoir gas housing 204 from the second chamber 324 as shown in FIGS. 6A and 7A. none. When an appropriate signal is received from a sensor or sensor 14 indicating to inflate the airbag or safety bag 18, the initiator 228 is actuated to rupture the first sealing disk 236 and ignite or boost the bill 240. Burns, which ignites propulsion pellets 258. Combustion of the propellant granules 258 produces a propellant gas in the first chamber 254 that flows into the second chamber 324 of the gas generator housing 212 and the storage gas housing 204. Due to the presence of high heat propulsion gas in the first chamber 254 and due to the introduction of high heat propulsion gas into the second chamber 324 and the storage gas housing 204, the pressure in this "vessel" increases correspondingly. do.

In order to rupture the second sealing disk 290 at an appropriate time and to initiate flow into the airbag or safety bag 18 (FIG. 1), the pressure increase rate in the second chamber 324 is increased by The introduction is designed to be greater than the rate of pressure increase in the reservoir gas housing 214. This pressure difference is caused by the storage gas housing 204 from the second chamber 324 in this region as shown in FIGS. 6B and 7B by fitting the valve 320 in contact with the interior of the second housing 278. It isolates and performs a rapid pressurization of the second chamber 324. Since the supply of pressurized medium is maintained to react with the propellant gas, the amount of pressurized medium in the second chamber 324 in the stationary state may be reduced before forming direct fluid communication between the reservoir gas housing 204 and the second chamber 324. Sufficient to react with the propellant gas introduced into the second chamber.

Once the pressure in the second chamber 324 reaches a predetermined magnitude, a second flow is formed through the gas generator outlet 286 toward the diffuser 298 and the airbag or safety bag 18 (FIG. 1). Hydraulic pressure applied directly on the sealing disk 290 ruptures the second sealing disk 290 as shown in FIG. 6C. However, valve 320 continues to impede flow from reservoir gas housing 204 into second chamber 324 by blocking gas generator outlet 316 as shown in FIGS. 6C and 7C. After a predetermined pressure difference is formed between the reservoir gas housing 204 and the second chamber 324, it is positioned away from the gas generator inlet 316 so as to be shown in FIGS. 6D and 7D, A pressurized medium flows from the reservoir gas housing 204 toward the second chamber 324. For example, due to the structure shown for the valve 320 (e.g., a metal foil of cylindrical rule), the front of the valve 320 may be described above in a region close to or aligned with the gas generator inlet 316. Collapsing or moving radially in the vehicle. However, the front portion of the valve 320 remains attached to the second housing 278.

Based on the foregoing, the design of the inflator 202 includes the aforementioned propellant (e.g., casing synthesizer) and pressurized medium (e.g., a mixture of oxygen and at least one inert gas). It improves the performance of your system and is particularly suitable for use with this system. For example, when the aforementioned propellant and the pressurized medium are used, secondary combustion of the propellant gas by the pressurized medium is performed in the second chamber 324. This additional combustion further expands the gas, which reduces the amount of propellant gas required and reduces the weight of the expander 202. This secondary combustion also reduces the toxicity of the propellant gas. By employing a "long" second chamber 324, in particular by using the distance between the closure of the late combustor 274 and the gas generator inlet 316 with respect to the gas generator outlet 286, the synthetic flow is airbag or abutment. There is sufficient time for secondary combustion to occur before being fed to the bag 18 (FIG. 1).

As noted, in any design, the inflator 202 may be formed in the manner described above without using the valve 320. This is possible by using a propellant and a pressurized medium in the manner mentioned above. That is, such a propellant is mixed with a calcination pressurized medium (e.g., a mixture of oxygen and an inert fluid such as at least one type of inert gas) to produce a propellant gas that can be burned again in the second chamber 324. do. In this case, secondary combustion of the gas resulting from the "secondary" combustion of the propellant gas in the second chamber 324 and the ignition or ignition of the booster material 240 is sufficient to not require the valve 320. Form pressure increase or rate of increase. For example, secondary combustion causes at least about 30%, and preferably about 50%, of pressure increase in the second chamber 324 after operation of the expander 202. As such, the use of a chemical reaction in the second chamber 324 can be used to achieve rapid pressurization based flow initiation, thereby reducing the need for use of the valve 320.

Another embodiment of a composite expander that can be used in the expansion safety device 10 of FIG. 1 is shown in FIGS. The inflator 350 functions and operates in a similar manner to the inflator 202 described above, but it is specifically configured for application on the driver's side. As such, the expander 350 includes in particular an inert fluid such as propellant (eg, casing propellant, synthetic propellant) and a composite element pressurized medium (eg, oxygen and at least one inert gas) in the aforementioned manner. To improve the performance of the inflatable device 10.

Mainly referring to FIG. 8, the composite inflator 350 includes a central housing 358 that includes two main components, a gas generator 362 and a diffuser 458, and a storage gas housing 354. . The reservoir gas housing 354 is preferably attached circumferentially around the central housing 358 in an appropriate manner (eg, via welding 442, 450) to achieve a hermetic seal. The storage gas housing 354 is formed in a sulfur shape and accommodates a pressurized medium. Again, the main advantage of the inflator 350 is that the first advantage of the inflator 350 is achieved by rapidly pressing the area adjacent to the second sealing disk 428 (isolating the flow between the inflator 350 and the airbag or safety bag 18 (FIG. 1)). Hydraulic pressure is directly applied to this to "open" the two sealing disks 428. In addition, as described in detail below, another advantage of inflator 350 is to concentrate significant increases in pressure that are primarily associated with the operation of the composite within gas generator 362. Thus, the wall thickness of the reservoir gas housing 354 can be reduced compared to the design of a conventional composite expander (ie, the pressure ratio of the reservoir gas housing 354 can be reduced) and thus the expander 350 ) Weight is reduced.

The central housing 358 is arranged about the central longitudinal axis 352 of the inflator 350 and includes a gas generator 362 and a longitudinally spaced diffuser 458. The gas generator 362 and the diffuser 458 are at least partially formed by this central housing 358. For example, the gas generator 362 may include a cylindrical gas generator housing 366 defined by a portion of the central housing 358, an igniter assembly holder 370, a domed partition 390, and a gas generator end cap assembly. 420 is included. In particular, since the gas generator housing 366 accommodates a large amount of pressurized medium in a stationary state, the igniter assembly holder 370 has a lower portion of the central housing 358 and the storage gas housing 354 in order to achieve a desired hermetic sealing. Is connected in an appropriate manner (eg, via welding 442). The igniter assembly holder 370 can be used with an O-ring 372 to secure a suitable ignition assembly 374 (eg, an electrically actuated tube or other suitable flame igniter) and to provide a sealing interface. In order to isolate the igniter assembly 374 from the pressurized medium in the gas generator 362, the first sealing disk (second sealing disk) 378 is ignited in an appropriate manner (eg, via welding 446). Attachment to the ends of the assembly holder 370 forms the desired hermetic seal. In the illustrated embodiment, the first sealing disc 378 is held between the igniter assembly holder main housing 382 and the igniter assembly end cap 386 of the igniter assembly holder 370 at the welding point 446.

The partition wall 390 separates the gas generator housing 366 into the first chamber 394 and the second chamber 418. The first chamber 394 is defined by the bottom of the central housing 358, the igniter assembly holder 370, and the bottom surface of the partition wall and is arranged adjacent to the igniter assembly 374. The first chamber 394 of the gas generator housing 366 houses a propulsion pellet 404 that generates a propellant gas to increase flow to the airbag or safety bag 18 (FIG. 1) upon ignition. . Thus, the first chamber 394 can be characterized as a propulsion chamber. 0.5 wt% to 5.0 wt% of hydroxypropyl cellulose is added in place of appropriate ignition or booster material 408 (eg, 0.5 wt% to 5.0 wt% RDX and aluminum to aid in ignition of the propellant granules 404). 89 wt% RDX, RDX having 11 wt% aluminum powder or aluminum booster material) can be positioned in the center of the first chamber 394 in line with at least a portion of the igniter assembly 374. Suitable screens 412, booster cups, and the like, separate propellant pellets 404 from ignition or booster material 408.

The first chamber 394 is stored in the stationary gas by at least one supply orifice or hole 400 (two in the illustrated embodiment) such that the pressurized medium is received in the first chamber 394 as previously mentioned. In fluid communication with the housing 354. In the illustrated embodiment, the feed hole 400 extends radially in a substantially horizontal form (i.e. contained in a plane perpendicular to the central axis 352). (I.e. extending along a radius starting at the central longitudinal axis). As mentioned above with respect to the expander 202, the size and number of the supply holes 400 may be arbitrarily selected to adjust the performance of the expander 350.

As described in more detail below, the reaction of syngas from ignition or ignition of the booster material 408 may chemically react with the pressurized medium to further increase the rapid onset of pressurized flow of the expander 350.

Part of the propulsion gas from the first chamber 394 towards the storage gas housing 354 to achieve the desired output or discharge towards the airbag or safety bag 18, ie to achieve the desired expansion rate of the airbag or safety bag 18. Can spill. In particular, it is preferable to supply the propellant gas to the storage gas housing 354 at a rate that maintains a substantially constant flow of fluid from the storage gas housing 354 into the second chamber 418 for a sufficient time as described below. . Typically, only a portion of the propulsion gas generated during operation to achieve the desired result (e.g., less than about 40% of the flow rate of the propulsion gas, typically less than about 30% flows into the storage gas housing 345). It needs to flow into this storage gas housing 354.

When feed hole 400 is used, the pressure increase in storage gas housing 354 after ignition of propulsion pellets 404 is significantly lower than in most commercial composite designs. That is, the significant pressure increase primarily associated with the ignition of the propulsion kernel 404 is almost limited to the gas generator 362. Thus, the need for strength of the reservoir gas housing 354 can be reduced. This makes it possible to reduce the wall thickness for the reservoir gas housing 354 or lightweight material and these reduce the weight of the inflator 350. For example, an internal pressure of about 4000 psi (2.8 10 ⁶ kg / m ² ) and when the housing 354 is made of mild steel, the maximum wall thickness required for the storage gas housing 354 is about 0.075 inches (0.19 cm).

At least about 50% of the total propellant flow rate, and more generally about, from the first chamber 394 to the second chamber 418 (also known as a post-combustor as described below). 70%) is formed. The second chamber 418 of the gas generator housing 366 is the first of the gas generator housing 366 by at least one propulsion 416 (shown in two) extending through the gas generator partition 390. Fluid is in communication with the chamber 394. As will be described in more detail below, the main flow path of the pressurized medium from the reservoir gas housing 354 towards the safety bag or air bag 18 is directed into the second chamber 418. To induce sufficient "mixing" of the propellant gas flowing from the first chamber 394 into the second chamber 418 by means of a pressurized medium flowing from the reservoir gas housing 354 into the second chamber 418 (eg In order to receive the gas for a suitable time, the propulsion port 416 is oriented to induce a vortex-like motion in the second chamber 418 (eg, induced by the velocity component of at least one yarn). Can be One way to induce this vortex motion is to direct the nearly linearly associated gas generator propulsion 416 in the manner shown in FIG. These propellants 416 are "tilted" in opposite directions within each reference plane.

The second chamber 418 of the gas generator housing 366 is longitudinally aligned with the first chamber 394 and the storage gas housing 354 is arranged circumferentially about this, so that the gas is generated by the partition wall 390. It is separated from this. The second chamber 418 is defined by the middle portion of the central housing 358, the gas generator septum 390, and the gas generator end cap assembly 420. The gas generator end cap 420 is attached to the central housing 358 in an appropriate manner (eg, via welding 454), and the top of the central housing is in an appropriate manner (eg, welding 450). Through the storage gas housing 354). Preferably, the welding points 450 and 454 form a hermetic seal since the second chamber 418 receives a large amount of pressurized medium in a stationary state. Gas generator end cap 420 includes at least one gas generator outlet 424 (shown as one). In order to receive the pressurized medium in an inflator 350 and in particular in the second chamber 418 until the desired time is reached, the second sealing disk 428 is adapted to achieve a desired hermetic seal (eg, welding 454). The second sealing disk 428 is in a suitable manner (e.g., overlapping between the upper gas generator end cap 421 and the lower gas generator end cap 422) and gas generation is applied to the end cap assembly 420. Attached.

Based on the fluid transfer between the first chamber 394 and the second chamber 418, the gas produced by the ignition or booster material 408 as well as the propellant gas produced by the combustion of the propellant grains 404. At least a portion of is introduced into the second chamber 418. Due to the rapid increase in pressure in the second chamber the flow from the inflator 350 flows into the diffuser 458 and then into the airbag or safety bag 18 (FIG. 1) when controlled in the manner described below. The two hermetic disc 428 opens at the appropriate time. The diffuser 458 uses a plurality of diffuser holes 462 to provide a relatively non-propulsive output to the airbag or safety bag 18. Diffusion screens (not shown) in diffuser 458 may be used to retain the ruptured disk portion in inflator 350 or to further promote mixing or reaction of the propellant gas and pressurized medium prior to passing through airbag or safety bag 18. Can be included.

The second chamber 418 is also in fluid communication with the storage gas housing 354. In this regard, at least one of the plurality of gas generator inlets 432 may include the storage gas housing 354 and the second so that the pressurized medium from the storage gas housing 354 enters the second chamber 418 at an appropriate time. Fluid is communicated between the chambers 418. That is, in the case of any design or application, this particular flow can be controlled with respect to the direction of flow. In particular, valve 438 may be located adjacent to at least one and preferably multiple gas generator inlet 432. At rest, the valve 438 does not need to actually isolate the reservoir gas housing 354 from the second chamber 418 in this zone. In practice, a large amount of pressurized medium is preferably contained in the second chamber 418 at rest so that the unsealed contact surface receives the supply of pressurized medium. One shape for the valve 438 that does not isolate the second chamber 418 from the storage gas housing 354 over the inlet 432 is a large rolled shape (e.g., 0.002 inch (0.005 cm) thick). A cantilever connection may be used between the stainless steel valve 438 and the interior of the gas generator housing 366. That is, the rear portion of the valve is retained between the central housing 358 and the partition wall 390 without the front portion of the valve 438 attached, so as to freely move or deflect the valve 438 to provide an actuation capability. You can. Although reference has been made to the form of the valve 438, each plug 438a, 438b (FIGS. 14A, 14B) may be arranged at each inlet 432. As shown in FIG. Preferably, such plugs 438a and 438b are connected to inflator 350 by tethers 439 and the like (shown only in FIG. 14B). It is preferable to support the plugs 438a and 438b in the inlet 432 with the flexible member 433 (Fig. 14A). These plugs 438a, 438b can also be used for the other synthetic inflators described herein.

Referring to the above description, the pressure across the reservoir gas housing 354 and the gas generator 362 in a stationary state may be formed substantially the same. However, after an operating state or ignition of the propulsion pellets 404, the pressure across the various chambers of the inflator 350 are formed differently to achieve the desired performance. In this regard, upon ignition of the propellant pellets 404, propellant gas begins to flow into at least the second chamber 418 to increase the pressure therein. If at least one feed hole 400 is integrated in the design, a small amount of propellant gas is introduced into the reservoir gas housing 354 to increase the pressure therein. Preferably, the rate of pressure increase in the second chamber 418 is higher than the rate of pressure increase in the reservoir gas housing 354 due to the introduction of propellant gas therein and the respective volume. This pressure difference causes the valve 438 to compress in contact with the interior of the alignment of the gas generator housing 366 and thus cover the gas generator inlet 432 so that the reservoir gas housing ( 354 is isolated. When the second chamber 418 is at a pressure level, the hydraulic pressure opens, ruptures, or breaks the second sealing disk 428. This thus initiates the flow of fluid from the gas generator 362 towards the diffuser 458 and then towards the airbag or safety bag 18.

As can be appreciated, valve 438 initiates flow of fluid toward airbag or safety bag 18 at a suitable time. In particular, for any design, the use of the valve 438 can pressurize the second chamber 418 at a rate that opens the second sealing disk 428 at an appropriate time. If the valve 428 is used in the expander 350, the propellant gas is introduced into the storage gas housing 354 from the second chamber 418. As such, it takes a long time to increase the pressure in the second chamber 418 to the stage of rupturing the second sealing disk 428. However, the second chamber 418 can be used to make the pressurized chamber compact, thus reducing the time required to initiate the introduction of fluid into the airbag or safety bag 18 (FIG. 1). As described later, the propulsion pellets 404 or the ignition and booster material 418 may not be required for satisfactory operation (e.g., to promote rapid pressurization in the second chamber 418). By utilizing the combustion of the gas produced by the combustion) the volume of the second chamber 418 can be provided in a sufficiently small form in any design manner or the propellant and the pressurized medium can be chosen at random.

The valve 438 is positioned in place and shuts off the gas generator inlet 432 for a predetermined time after the second sealing disk 428 is opened to initiate flow towards the airbag or safety bag 18. Nevertheless, once a predetermined pressure difference is formed between the reservoir gas housing 354 and the second chamber 418, the upper free end of the valve 438 is moved by this pressure difference to expose the gas generator inlet 432. The fluid flow from the storage gas housing 354 into the second chamber 418 is then initiated. The lower end of the valve 438 remains attached to the gas generator housing 366. When the valve 438 is largely shaped, the valve can move radially inward toward the central axis 352 and also cause collapse of the valve 438 in a region radially aligned with the gas generator inlet 432. Of the desired flow is allowed.

The primary function of the second chamber 418 is to provide or allow efficient mixing of the propellant gas and the pressurized medium after breaking the second sealing disk 428 through rapid pressurization technique and before discharging it toward the airbag or airbag 18. . In case of using the above-mentioned propellant mixture (e.g., shell-type propellant, synthetic propellant) and the aforementioned pressurized medium (e.g. mixture of oxygen and inert fluid such as at least one inert gas). This mixture, in turn, burns the propellant gas again to provide the benefits as noted (e.g., reduced toxicity, reduced further combustion and associated potential increases in cost). As such, the second chamber 418 is characterized as a post-combustor. Preferably, at least about 99% of the propellant gas and the ignition or booster material gas, and preferably about 100% of the combustion, occur in the expander 350. This reduces the likelihood of damage to the airbag or safety bag 18 (FIG. 1).

Due to the restrictions imposed on the driver's side, it is not possible to use the "long" second chamber 418 as in the case of the inflator 202 to provide the functionality of a postcombustor. To compensate for the use of the "short" second chamber 418 when applying the inflator 350 to the driver side, the second chamber 418 from the reservoir housing 354 to promote mixing of the pressurized medium and the propellant gas. The mixing of the propellant gas and the pressurized medium in the second chamber 418 can be further enhanced by introducing a vortex flow into the flow (primarily a pressurized medium, or a large amount of propellant gas and ignition or booster material gas). This extends the time for chemical reaction by retaining the propellant gas and the pressurized medium in the second chamber 418.

One way of introducing the above-mentioned vortex type motion is to direct the gas generator inlet 432 almost straight in the reference horizontal plane, the axis of which inlet 432 is inflator 350, as shown in FIG. It does not pass through the central longitudinal axis 352 of. That is, such a substantially straight inlet 432 does not protrude outward from the central longitudinal axis 352 along the radius to connect the second chamber 418 and the reservoir gas housing 354 to each other. Instead, a portion of this inlet 432 is arranged in a radial position, while the other portion is arranged in another radial position. As such, the flow from the reservoir gas housing 354 into the second chamber 418 is formed in the direction of the arrow of FIG. In order to further promote the mixing of the propellant gas and the pressurized medium, the gas generator inlet 432 may be directed toward the point where the gas generator inlet 432 meets the interior of the second chamber 418.

In the case of inflator 350, the design dimensions given may vary. In particular, the capacity of each chamber of inflator 350 depends on the application of the inflator. For example, in at least one situation related to the present invention the capacity of the inflator housing can range from about 50 cm ³ to about 150 cmm ³ . The capacity of the first chamber 394 can range from about 1 cm ³ to about 15 cm ³ . The capacity of the second chamber 418 can range from about 1 cm ³ to about 20 cm ³ . In the following, dimensions are provided for embodiments having performance characteristics similar to those described below. 1) The diameter of the inflator 350 is about 3.25 inches (8.26 cm). 2) The height of the central housing 358 is about 1.6 inches (4.06 cm). 3) The height of the reservoir gas housing 354 is about 1.2 inches (3.05 cm). 4) The interior volume of the reservoir gas housing 354 is about 5 cubic inches (81.94 cm ³ ). 5) The internal volume of the first chamber 394 of the gas generator housing 366 is about 7 cm ³ (7 cc). 6) The internal volume of the second chamber 418 of the gas generator housing 366 is about 2 cm ³ (2cc). 7) Two supply holes 400 are provided, each having a diameter of about 1.5 mm. 8) Two propulsion holes 416 are provided, each having a diameter of about 2 mm. 9) The total weight of the propellant pellets 404 is about 3.5 grams and has a mixture of the aforementioned manner including RDX, CA, TMETN and stabilizers. 10) The static pressure in the reservoir gas housing 354 is about 400 psi (2.8) so that about 40 grams of pressurized medium is present. 10 ⁶ kg / m ² ), about 85% argon and about 15% oxygen in this pressurized medium (in moles). 11) The expander 350 is made of mild steel. 12) The wall thickness of the reservoir gas housing 354 is about 0.075 inches (0.19 cm) and about 18000 psi (12.6). 10 ⁶ kg / m ² ) pressure rate (burn rate). 13) The wall thickness of the central housing 358 is about 0.0625 inches (0.159 cm). 14) The total weight of the inflator 350 is about 400 grams.

Operation of inflator 350 is summarized with reference to FIGS. 11A-11D. When an appropriate signal is received from the sensor or sensor 14 (FIG. 1), the igniter assembly 374 is actuated to rupture the first sealing disk 378 and ignite the igniter or booster material 408, which is the 11A. Ignite the propulsion granules 404 as shown in the figure. Combustion of the ignition kernel 404 produces a propellant gas in the first chamber 394, which is the second chamber of the reservoir gas housing 354 and the gas generator housing 366 in which the propellant gas is mixed with the pressurized medium. 418 flows into. Due to the presence of the high temperature propellant gas in the first chamber 394 and due to the introduction of the high temperature propellant gas into the second chamber 418 and the reservoir gas housing 354, the pressure in this "vessel" correspondingly increases. do.

In order to rupture the second sealing disk 428 at the appropriate time and to start the flow towards the airbag or safety bag 18, the rate of pressure increase in the second chamber 418 is determined by the introduction of high temperature propellant gas and the respective volume. Due to this is designed to be formed higher than the pressure increase rate in the storage gas housing 354. This pressure difference inserts a valve 438 in contact with the interior of the gas generator housing 366 to isolate the reservoir gas housing 354 from the second chamber 418 in the region as shown in FIG. 11A. Since the supply of the pressurized medium is maintained to react with the propellant gas, the amount of pressurized medium in the second chamber 416 in the stationary state is exerted prior to forming fluid transfer between the storage gas housing 354 and the second chamber 418. It should be sufficient to react with the propellant introduced into the system.

Once the pressure in the second chamber 418 approaches a predetermined magnitude, this pressure is directed to FIG. 11B such that flow is formed through the gas generator outlet 424 toward the diffuser 458 and the airbag or safety bag 18. As shown, the second sealing disk 428 is ruptured. However, valve 438 continues to direct flow from storage gas housing 354 into second chamber 418 by blocking gas generator inlet 432. After a predetermined pressure difference is formed between the reservoir gas housing 354 and the second chamber 418, the force moves the valve 438 away from the gas generator inlet 432 or deflects it to remove it from the reservoir gas housing 354. It forms a flow of pressurized medium towards the two chambers 418. For example, the one-way check valve 438 is located close to or in line with the gas generator inlet 432 by the structure shown for the valve 438 (eg, a roll of wood). Collapses under the previously mentioned pressure differential. As mentioned above, in order to promote the mixing of the pressurized medium and the propellant gas continuously supplied to the second chamber 418 through the first chamber 394, the pressurized medium and the propulsion medium introduced into the second chamber 418. The flow of gas can be formed in a vortex. This flow increases the time that this mixture is held in the second chamber 418 before being supplied to the airbag or safety bag 18.

The pressure curve of the experimental model of the aforementioned embodiment with similar dimensions and other characteristics is shown in FIG. This curve is similar to that shown in FIGS. 13A-13D as described in more detail below. Initially, the static pressure in inflator 350 is about 4000 psi (2.18) 10 ⁶ kg / m ² ). At time T1 (about 5 ms), inflator 350 is activated and propulsion pellets 404 are ignited. As such, the propellant pellets 404 increase the pressure in the first chamber 394, the reservoir gas housing 354, and the second chamber 418, respectively. The maximum pressure in the first chamber 394 and the second chamber 418 is formed at about time T2 and at the moment when the rupture of the second sealing disk 428 occurs. At time T2 (about 1 after operation 10 ^-3 seconds), the pressure in the first chamber 394 is about 4000 psi (2.18) 10 000 kg (70.2) from standstill of 10 ⁶ kg / m ² ) 10 ⁶ kg / m ² ), and the pressure in the reservoir gas housing 354 is about 4000 psi (2.18) Approx. 4500 psi (3.16 from 10 ⁶ kg / m ² ) at rest 10 ⁶ kg / m ² ).

After the second sealing disk 428 is opened, the pressure in the second chamber 418 drops. At time T3, the pressure difference between storage gas housing 354 and second chamber 418 is sufficient to open valve 438 such that the pressure in gas generator inlet 432 increases again to increase pressure in second chamber 418. ). That is, after time T3, it is in flow from the reservoir gas housing 354 and the first chamber 394 into the second chamber 418. The pressure in the second chamber 418 is about 4750 psi (3.33) at time T4. 10 ⁶ kg / m ² ) increases to the maximum and then decreases. This is about 5000 psi (3.5) in the reservoir gas housing 354. 10 ⁶ kg / m ² ) almost coincide with the moment at which the maximum pressure is present. As such, the pressure increase in inflator 350 is primarily concentrated in gas housing 362 as compared to stored gas housing 354. Thus, the wall thickness of the reservoir gas housing 354 can be reduced as noted. Moreover, since the pressure in the second chamber 418 is relatively constant (about 400 psi (2.18) 10 ⁶ kg / m ² ) to 400 psi (3.22 Only varying between 10 ⁶ kg / m ² ), the desired output can be supplied to the airbag or safety bag 18.

As noted, in any design, the inflator 350 may be formed in the aforementioned manner without using the valve 438. This is possible by using a propellant and a pressurized medium in the manner mentioned above. That is, such propellant may be further combusted in the second chamber 418 by mixing with the oxidizing pressurizing medium (eg, a mixture of inert fluids such as inert gas, such as at least one type of argon, nitrogen, and oxygen). To generate additional gas. In this case, secondary combustion of the gas due to ignition or ignition of the booster material 408 in the second chamber 418 and "secondary" combustion of the propellant gas form a sufficient rate of pressure increase so that the valve 438 is necessary. Not. For example, secondary combustion causes at least about 30% and about 50% of the rate of pressure increase in the second chamber 418 after the inflator 350 is actuated. As such, it is possible to perform flow initiation by rapid pressurization using a chemical reaction in the second chamber 418, thus reducing the need for the valve 438.

In the case of the inflator 350 formed in the above-mentioned manner without the valve 438, the pressure curve and the airbag or safety bag 18 in the first chamber 394, the second chamber 418 and the storage gas housing 354 are Pressure curves in the fixed wall vessels shown are shown in FIGS. 13A to 13D, respectively. As can be seen by comparing FIGS. 12 and 13A to 13C, comparable performance is obtained without using the valve 438. This may mainly contribute to the use of a certain type of propellant and pressurized medium to provide combustion of gas in the second chamber 418, thus creating rapid pressurization in the second chamber 418 to open the second sealing disk 428. Can be executed.

In figure 15 a modified embodiment of the inflator according to the invention is shown. The modified inflator has a structure similar to the inflator shown in FIG. Thus, descriptions of similar structures are omitted, but they may refer to the same reference numerals as those shown in the inflator of FIG. Any difference between the modified inflator of FIG. 15 and the inflation period of FIG. 5 is described below.

The first chamber 501 has an inner diameter larger than the inner diameter of the second chamber 502. The length of the second chamber 502 is significantly smaller than the length of the second chamber 324 of FIG. Thus, the second chamber 502 has a much smaller capacity than the capacity of the first chamber 501. In this embodiment, the capacity of the second chamber 502 is about 1/20 of the capacity of the first chamber 501.

The delivery tube 503 is located on the axis of the first chamber 501 and connects the initiator 228 to the suction nozzle 274. The delivery tube 503 is hollow and has a plurality of connecting holes 504 in its peripheral wall. The delivery tube 503 and the suction nozzle 274 provide fluid transfer between the first chamber 501 and the second chamber 502 (eg, an axial path between the foaming agent 228 and the disk 290). The first sealing disc 236 closes the passageway 507 formed between the initiator 228 and the first chamber 501.

The second chamber 502 is connected to the outlet 286 by a late combustor pipe 505. The second chamber 502 located near the second chamber 502 and the suction nozzle 274 vertically closes the outlet 286 through the pipe 505. The supply hole 262 communicates the first chamber 501 and the storage gas housing 204. Since the valve 320 is in intimate contact with the inner wall of the second chamber 502, the inlet 316 is opened in a stopped state.

In the stationary state, the pressure of the reservoir gas housing 204, the first chamber 501, and the second chamber 502 is defined by the suction nozzle 274, the transfer tube 503, and the supply hole 262. . In this state, upon operation of the initiator 228, the first sealing disk 236 ruptures and the propellant pellets 258 burn. Combustion gas generated from the propulsion pellets 256 increases the pressure in the first chamber 501 to increase the pressure in the second chamber 502 through the delivery tube 503 and the suction nozzle 274. The increased pressure moves through the valve 320 toward the second chamber 502 to close the inlet 316. Combustion gas is injected from the suction nozzle 274 toward the pipe 505 to rupture the second sealing disk 290.

At this time, the pressure in the second chamber 502 is temporarily increased to allow the valve 320 to open the inlet 316. Therefore, the pressurized medium flows into the second chamber 502 and the pipe 505 through the inner hole 316. The oxygen component in the pressurized medium reacts with carbon monoxide and hydrogen in the combustion gas to convert them into carbon monoxide and water vapor in the second chamber 502 and the pipe 505. Water vapor and argon in the pressurized medium are supplied to the airbag (not shown) through the outlet 286 and the diffuser 508 to inflate the airbag.

As mentioned above, in this embodiment, the second chamber 502 is formed smaller than the first chamber 501. In addition, the first sealing disk 290 is located near the suction nozzle 274. Thus, in addition to the same effects and advantages as the inflators shown in FIGS. 5 and 8, in this embodiment, an increase in the pressure of the first chamber 501 and the second chamber 502 occurs rapidly, so that the disk 290 It bursts quickly.

The delivery tube 503 with multiple holes 504 increases the flow rate of the combustion gas as it passes through the holes 504. This helps to rupture the disk 290 quickly.

It is noted that the delivery tube 503 can also be applied to the embodiment shown in FIG. Further, with regard to the opening area of each suction nozzle shown in FIGS. 5 and 8, and the total opening area of the suction hole, whether or not the pressurized medium or the propellant gas is introduced into the first chamber. Thus, one of the two can be determined larger than the other.

Table 2 shows the physical properties of the inflator shown in FIGS. 5, 8 and 15 that can be suitably used in conjunction with at least one aspect associated with the present invention. Table 2 shows, for example, the range of values of the propulsion granules, the pressurized gas and the pressurized medium.

TABLE 2

Another embodiment of a composite inflator that can be used in at least one form of the invention and that can be incorporated into the inflated safety device 10 of FIG. 1 is shown in FIG. 16. The inflator 614 is a cylindrical inflator housing 622 containing a pressurized medium 620 supplied to a safety bag or airbag 18 (FIG. 1) and a pressurized medium 620 to increase flow towards the airbag 18. And a gas generator 624 that produces a propellant gas to expand the cavities.

The inflator 614 can be used as a side impact inflator (eg, used to protect passengers when the vehicle is in a side impact) and can be attached to the seat or door of the vehicle. The pressurized casing 620 may comprise an inert fluid (eg argon) and oxygen and a propellant in the manner described above may be used.

A gas generator housing 644 is welded to the right buttonhole 642 of the inflator housing 622, a portion of which is arranged in the inflator housing 622. Within the container chamber 654 of the gas generator housing 644 is housed a propellant 646 (eg, in the manner described above) that generates propellant gas upon combustion and a propellant igniter assembly 648 is arranged. have. Gas generator housing 644 and propulsion igniter assembly 648 are arranged on longitudinal axis 617 of inflator housing 622.

Propellant 646 can be a nitramine propellant, for example, about 70 wt% RDX (hexahydrotrinitrotriazine), about 5 wt% to about 15 wt% cellulose acetate, and about 5 wt% to about 15 wt% GAP (glasses azide polymer). Propellant 646 produces a combustible gas comprising carbon monoxide and hydrogen upon ignition.

The gas generator housing 644 includes a communication hole 650 at its inner end which is mainly blocked by the first disk 652. The ring connector 626 is welded to the left buttonhole 625 of the inflator housing 622. The cup diffuser 630 is fixed to the left end hole 628 of the connector 626. The diffuser 630 includes a peripheral wall 630a with a plurality of holes 632 and an upper wall 630b. This diffuser 630 is arranged on the shaft 617 and in fluid communication with the airbag 18 (FIG. 1).

The right buttonhole of the connector 626 forms the outlet 634 of the inflator housing 622. A second disk 636 that vertically blocks the outlet 634 is arranged at the outlet 634. The diffuser 630 includes a hole 630c in fluid communication with the outlet 634. A cover 640 with a plurality of holes 638 is attached to the connector 626 to cover the outlet 634. Thus, the inner inflator housing 622 is vertically closed by two disks 636 and 652 and the peripheral wall of the inflator housing 622. The container chamber 645 is in fluid communication with the interior of the inflator housing 622 by a communication hole 650, while the interior of the inflator housing 622 has an opening when the first and second disks 652, 636 rupture. 638 is in fluid communication with the outlet 643.

In one embodiment, the distance between the first disk 652 and the second disk 636 is about 20 mm to about 70 mm. The amount of pressurized medium 620 in the inflator housing 622 is in the range of about 40 cm ³ to about 100 cm ³ . In one embodiment, the amount of pressurized medium 620 in the inflator housing 622 is preferably about 50-90 cm ³ . The pressure inside the inflator housing 622 is about 4000 psi (2.18) 10 ⁶ kg / m ² ).

When the propulsion igniter assembly 648 is actuated in response to a signal from the detector 612, the propellant 646 ignites to produce a combustible gas. Combustible gases include carbon monoxide and hydrogen. Combustible gas increases the pressure in the gas generator housing 644 to rupture the first disk 652. At this time, the combustible gas is introduced into the inflator housing 622 through the communication hole 650 and mixed with the pressurized medium 620.

The pressurized medium 620 contains oxygen that reacts with carbon monoxide and hydrogen in a combustible gas to produce carbon dioxide and water groups. Combustible gas increases the pressure in the inflator housing 622 that acts on the second disk 636 through the aperture 638. In other words, the gas should cover the inlet 640 into the hole 638 around the end wall 614. This promotes more complete combustion in the housing 622. Thus, the end wall 641 may function as a propellant trap arranged at the outlet for the inflator 614. That is, because the wall 641 of the lid 640 is located on the longitudinal axis 617, the propellant gas that ruptures the first disk 652 is not directly injected into the second disk 636. After the propellant gas has sufficiently reacted with the pressurized medium in the housing 622, the gas ruptures the second disk 636 through the holes 638 on the peripheral wall of the lid 640. Thus, the carbon monoxide contained in the propellant gas passes through the outlet 634 after being oxidized.

The second disk 636 ruptures due to an increase in pressure on its main surface, and at the time of rupture, the second disk 636 is subjected to a high pressure to the airbag or safety bag 18 (FIG. 1) through the hole 632 of the outlet 634 and the diffuser 630. It supplies carbon dioxide, water vapor and an inert gas. The airbag or safety bag 18 (FIG. 1) inflate efficiently by a predetermined amount at a predetermined time.

As mentioned above, the first and second chambers 652, 636 and the diffuser 630 have expansions arranged on the axis 617 of the housing 622 such that the entire inflator can be formed in a compact cylindrical shape. have. Thus, the inflator can be firmly attached in a limited space, such as the interior of a door or seat of a vehicle, without modifying the shape of the door or seat.

In this embodiment, propellant 646 produces a combustible gas comprising carbon monoxide and hydrogen upon combustion. The combustible gas reacts with oxygen in the pressurized medium 620 and is transferred to carbon dioxide and water vapor. Thus, the airbag or safety bag 18 can be inflated by a gas that is almost harmless to the passenger.

The diffuser 630 is formed in a cup shape and includes a peripheral wall 630a and an upper wall 630b. The diffuser 630 also includes a hole 630c in fluid communication with the outlet 634 and a plurality of holes 632 in fluid communication with the hole 630c in the peripheral wall 630a. Thus, when gas is released from the inflator housing 622, the airbag or safety bag 18 can be efficiently inflated by the gas exiting from the plurality of holes 632 in all directions.

16A shows a modified example of the inflator of FIG. 16. In this embodiment, the gas generator housing 624 includes a base 660 and a chamber 662. Base 660 supports igniter assembly 648. Chamber 662 is arranged with a propellant and fitted together. The disk 664 is sealed through the hole 666 of the chamber 662. The chamber 652 is in fluid communication with the inflator housing 622 through a communication hole 650. Thus, the interior of chamber 652 is under pressure.

When the igniter assembly 648 is actuated, the igniter assembly 648 ruptures the disk 664 directly and ignites the propellant to produce combustible gas. The combustible gas reacts with oxygen in the pressurized medium 620 to convert carbon dioxide and water vapor. Thus, the airbag or safety bag can be inflated by the gas detrimental to the passenger.

The foregoing detailed description of the invention has been mentioned for purposes of illustration and description. Moreover, this description is not intended to limit the invention to the form mentioned herein. Therefore, within the scope of the present invention, those skilled in the art can make changes and modifications to the present invention as described above. The foregoing embodiments illustrate the invention in the best possible manner and are intended to enable those skilled in the art to utilize the invention in its various embodiments by various modifications necessary for the particular application or use of the invention. The appended claims are intended to cover other embodiments as permitted by the prior art.

1 is a schematic view of an inflatable safety device according to the invention.

2A and 2B are, respectively, longitudinal cross-sectional views of one embodiment of a composite expander and an enlarged view of a portion thereof.

3 shows the operating curve of inflator pressure versus time for the propulsion composite of Example 2. FIG.

4 shows the motion curve of receiving tank pressure versus time for the propulsion composite of example 2. FIG.

5 is a longitudinal sectional view of another embodiment of a composite expander.

6A-6D are longitudinal cross-sectional views showing the sealing disk and valve of the inflator of FIG. 5 at different times during operation.

7A to 7D are sectional views showing the valves of FIGS. 6A to 6D, respectively.

8 is a cross-sectional view of another embodiment of a composite expander.

9 is a cross-sectional view of the central housing taken along line 9-9 of FIG.

FIG. 10 is a plan view of the partition of FIG. 8 located between the first chamber and the second chamber of the gas generator housing, in particular showing the orientation of the propulsion.

11A-11C are enlarged longitudinal cross-sectional views showing the valve and sealing disk of the inflator of FIG. 8 at different times during operation.

FIG. 12 is a graph showing the pressure in the various chambers of the inflator of FIG. 8 during operation.

13A-13D are graphs showing the pressure in the various chambers of the inflator of FIG. 8 during operation when the valve and valve system are not used.

14A and 14B show cross-sectional views of another embodiment of the composite inflator valve of FIGS. 5 and 8, respectively.

15 is a longitudinal sectional view showing yet another embodiment of the composite expander of the present invention.

16 is a longitudinal sectional view showing another embodiment of the composite inflator of the present invention.

FIG. 16A is a variation of the composite inflator of FIG. 16. FIG.

Explanation of symbols on the main parts of the drawings

10: safety device 14: detector

18: Airbag or safety bag 22: Conduit

30,202,350,614: Inflator 34,622: Inflator housing

36,620: pressurized medium 38,298,458,630: diffuser

40,634: discharge hole 46,228: initiator

50: Projectile 54: Barrier

58,104,226,304,412: Screen 66: Boss

74: orifice sleeve 78: orifice hole

86,212,366,644: Gas Generator Housing

90,258,404: Propulsion granule 94: Propulsion sleeve

96: gas generator housing end 98: gas generator suction nozzle

100,102: baffle 108: retainer

114,648 primer holder 120: collision primer

124: working piston 126: spacer

128: continuous frame projecting member 136: countersunk head washer

144,240,408: Ignition or booster material

204,354: storage gas housing 216: first housing

220: breeder 244: booster cup

248,308,312,442,450,446: Welding 254,394,501: First chamber

270: shoulder 274: afterburner nozzle

278: second housing 282: post-combustor adapter

286: gas generator outlet 290: second burst disk

358: central housing 360: gas generator

370: igniter assembly holder 372: first sealing disk

390: dome-shaped bulkhead 404: propulsion grain

418,502: second chamber 420: end cap

432: inlet 438: plug

433: flexible member 439: tether

503: delivery tube 504: communication hole

507: passage 505: late combustor pipe

Claims (25)

A composite inflator for an auto-expandable safety system comprising an air bag or safety bag, comprising: an inflator housing containing a pressurized medium, and a gas generator housing interconnected to the inflator housing, the gas generator housing propellant; A first chamber containing a first chamber, a propellant ignition assembly, a second chamber, an outlet, and a first sealing disk, the second chamber being propelled by a propellant ignited by the pressurized medium. Fluidly communicating with the first chamber and the inflator housing to combust gas, the outlet being arranged on the gas generator housing to supply pressurized medium and propellant gas from the second chamber toward an air bag or safety bag. And the first sealing disc shuts off the outlet normally. And rupture after ignition of the propellant, The first chamber, the second chamber and the first sealing disk are arranged on a common longitudinal axis of the composite expander, and the gas generator housing is configured to maintain the same internal pressure of the expander housing and the first chamber. And at least one supply hole for the composite inflator. In a composite inflator for an automatic inflatable safety device containing an air bag or safety bag, An inflator housing containing a pressurized medium, A gas generator interconnected with the inflator housing, the gas generator having at least one of communicating fluids between the first and second chambers, the propellant contained in the first chamber, and the fluid between the first chamber and the second chamber; A gas generator comprising a supply hole, at least one gas generator inlet for communicating fluids between the second chamber and the inflator housing, and at least one gas generator outlet; A first sealing disc located between all the gas generator outlets and the airbag or safety bag; A propellant igniter assembly in combination with the gas generator, the propellant igniter assembly in which propellant gas is generated by ignition of the propellant; and Means for opening the sealing disc to initiate flow towards the airbag or safety bag, the opening means comprising means for combusting the propellant gas in the second chamber, the propellant gas being the first seal A composite inflator characterized in that it acts directly on the disc. 3. The composite expander of claim 2, wherein said first chamber, said second chamber, and said first sealing disk are arranged in common with said longitudinal axis of said expanding agent. 3. A composite inflator according to claim 1 or 2, wherein said propulsion ignition assembly comprises an initiator. 4. The propulsion ignition assembly of claim 1 or 3, wherein the propulsion ignition assembly comprises a initiator and a second sealing disc that vertically blocks the interconnection of the initiator and the first chamber, the second sealing disc being the longitudinal axis. Composite inflator, characterized in that arranged on the. 4. The propulsion ignition assembly of claim 1 or 3, wherein the propulsion ignition assembly comprises an initiator, a booster material ignited by the initiator, and a second sealing disk, wherein the second sealing disk is a reciprocal between the first chamber and the initiator. Break the connection vertically and rupture upon ignition of the booster material, and the booster material and the second sealing disc are arranged on the longitudinal axis. The inflator of claim 1, wherein the pressurized medium is contained within the inflator housing in a manner surrounding the gas generator housing. 4. The composite inflator of claim 3 wherein the gas generator has a housing and the pressurized medium is contained within the inflator housing in a manner surrounding the gas generator housing. 9. The gas generator housing according to claim 7 or 8, wherein the inflator housing includes a storage gas housing and is formed in an annular shape, while the gas generator housing has a cylindrical shape, and the inflator housing is surrounded by the gas generator housing. Syngas expander, characterized in that arranged coaxially. 10. The syngas expander of claim 9, wherein a plurality of said supply holes are arranged radially with respect to said longitudinal axis. 10. The method of claim 9, wherein the first chamber and the second chamber are separated by a domed partition, the propulsion ignition assembly is arranged closely to the partition within the first chamber, and the propellant is the propulsion ignition. And a composite expander arranged around the assembly. 12. The method of claim 11, wherein the domed partition includes a plurality of communication holes for communicating fluid between each other of the first chamber and the second chamber, the communication holes are arranged obliquely with respect to the longitudinal axis. Composite inflator made. 10. The method of claim 9, wherein the capacity of the inflator housing is 50 cm 3 to 150 cm ^3, the capacity of the first chamber is 5 cm ³ to 15 cm ^3, and the capacity of the second chamber is 1 cm ³ to 20 cm ^3. Composite inflator. 10. The method of claim 9, wherein the second chamber comprises a plurality of inlets for introducing the pressurized medium into the second chamber, each inlet arranged to intersect a line extending from the longitudinal axis. Composite inflator. 15. The apparatus of claim 14, wherein the second chamber comprises valve means, the valve means after the propulsion ignition assembly is operated until the pressure in the inflator housing exceeds the pressure in the gas generator by a predetermined value. And a function of inhibiting flow between the inflator housing and the gas generator housing through the inlet. The gas generator housing of claim 7 or 8, wherein the inflator housing and the gas generator housing are formed in a cylindrical shape, the gas generator housing is included in the inflator housing, and both ends of the inflator housing are both ends of the gas generator housing. Composite inflator, characterized in that connected to each other. 17. The composite expander of claim 16, wherein a plurality of said supply holes are arranged radially with respect to said longitudinal axis. 17. The composite expander of claim 16, wherein a diffuser nozzle is arranged between the first chamber and the second chamber, wherein the diffuser nozzle discharges the propellant gas toward the first sealing disk. 19. The compound inflator according to claim 18, wherein the capacity of the inflator housing is set larger than that of the first chamber. 19. A composite expander as set forth in claim 18, wherein said second chamber includes an inlet for introducing said pressurized medium into said second chamber of a major surface portion of said diffuser nozzle. 19. A composite inflator according to claim 18, wherein the furthest end of the diffuser nozzle with respect to the outlet and the closest portion of the inlet are separated by a distance of 4 mm to 80 mm. 19. The apparatus of claim 18, wherein the second chamber includes valve means, wherein the valve means after the propulsion ignition assembly is operated until the pressure in the inflator housing exceeds the pressure in the gas generator by a predetermined value. And a function of inhibiting flow between the inflator housing and the gas generator housing through the inlet. 23. A composite inflator according to claim 22, wherein said valve means is made of a flexible material and arranged around said diffuser. 19. The method of claim 18, wherein the first chamber has a delivery tube located on the longitudinal axis, the delivery tube having a plurality of holes and connected with the diffuser nozzle, wherein the plurality of holes are the delivery tubes. And in fluid communication with the interior of the first chamber. 17. The synthesis of claim 16 wherein the capacity of the inflator housing is between 150 cm and 450 cm 3, the capacity of the first chamber is between 10 cm 3 and 40 cm 3 and the capacity of the second chamber is between 1 cm 3 and 50 cm 3. Inflator.