JPS6397496A - Device and method for throwing away parachute expansion mechanism - Google Patents

Abstract

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

Description

DETAILED DESCRIPTION OF THE INVENTION Field of the Invention The present invention relates to deploying a parachute following evacuation from an aircraft, and more particularly to separating a parachute deployment mechanism from a parachute once the parachute has begun to deploy. It relates to a disposal device for discarding. The forces generated by the lateral expansion of the parachute are transmitted to the sacrificial device, thereby actuating the decommissioning device to separate the deployment mechanism from the parachute.

BACKGROUND OF THE INVENTION An evacuation seat for propelling an aircrew out of an aircraft after evacuation from a damaged aircraft so that the aircrew can safely deploy a parachute and safely return to the ground. has been known for a long time. Typically, the deployment mechanism consists of a rocket or drogue parachute, or a combination thereof, which pulls the parachute from a container supported by a crew member or escape seat.

However, once the deployment mechanism has served its purpose, it is highly desirable to discard this mechanism from the parachute.

One reason for discarding this mechanism is that it tends to tangle the parachute. Another reason is that rockets are usually very hot and can explode with such force that they can burn the crew or scorch the fabric of the parachute. The third reason is to reduce the weight of the parachute tail by discarding the deployment mechanism.
This reduces the impact on the crew due to the inertial force generated when the parachute fully opens.

Although there have been many prior art attempts to provide advantageous and effective disposal devices, there have been many problems because they have been configured as snap cords or cord clippers activated by explosive devices.

For one thing, these devices tend to be heavy and bulky. Moreover, these devices tend to operate in an unreliable manner and at unreliable times. In this regard, it is important that the sacrificial device is activated after the parachute has been withdrawn from the container, but before the parachute is fully opened in order to reduce the impact experienced by the crew as outlined above.

Examples of these prior art disposal devices include the Stanley (Sta)
U.S. Pat. No. 3,433,440 to Sanley, U.S. Pat. No. 3,436,037 to Sanley, U.S. Pat.
l) is disclosed in US Pat. No. 3,726,499.

SUMMARY OF THE INVENTION It is therefore a primary object of the present invention to provide a disposable device for a parachute deployment mechanism that is easy to construct, adds little extra weight to the parachute device, and is not unduly bulky. It is.

Another object of the invention is to reliably and
The object is to provide such a disposal device that functions in a timely manner.

Another object of the invention is to provide such a disposal device that separates the deployment mechanism from the parachute after the parachute is withdrawn from the container, but before the parachute is fully opened.

Yet another object of the invention is to provide such a sacrificial device that is actuated in response to the opening of the parachute by a predetermined amount and is powered by the force generated by the lateral spread of the opening parachute.

The objectives described so far are achieved with a parachute deployment device that basically includes a parachute packed in a container, a deployment mechanism for withdrawing the parachute from the container, and a disposal device for discarding the deployment mechanism from the parachute. be done. The apparatus includes an actuation device coupled to the parachute and the sacrificial device for actuating the sacrificial device in response to opening of the parachute a predetermined amount.

More particularly, the actuation device includes a pair of lanyards and a pair of rings for transmitting forces generated by the lateral expansion of the parachute to the dissipation device.

The objects described above are also achieved by a method of deploying a parachute from a container and discarding a deployment mechanism from the parachute. The method includes pulling the parachute from the container by a deployment mechanism, initiating deployment of the parachute, and separating the deployment mechanism from the parachute in response to deployment of the parachute by a predetermined amount.

More specifically, the separating step uses force generated by the opening of the parachute to separate the deployment mechanism from the parachute.

Other objects, advantages, and salient features of the invention will become apparent from the following detailed description, which discloses preferred embodiments of the invention, taken in conjunction with the accompanying drawings.

DETAILED DESCRIPTION OF THE INVENTION Referring now to FIGS. 1-9, the present invention basically relates to a sacrificial device for releasably interconnecting a parachute 14 and a parachute deployment mechanism. It is directed to the actuating device 210 used. The actuating device 10 consists of a pair of lanyards 18 and 20 and a pair of rings 22 and 24 that transmit the forces created by the spreading of the opening parachute into the groove to the dumping device to dump the deployment mechanism 16. Since the actuating device does not use an explosive device or a cord cutter, it is light in weight and not bulky. Additionally, the actuation device utilizes the opening of the parachute to actuate the abandonment device, thereby ensuring that the deployment mechanism is abandoned after the parachute has been withdrawn from the container and after the parachute has begun to open. Thus, when the parachute fully opens, the inertial force experienced by the escaping crew member is reduced.

Referring now to FIGS. 1-4, the present invention is directed to an evacuation seat 26 used to evacuate an aircrew 28 from an aircraft 29, where the aircrew is
The main parachute 14 ultimately returns the vehicle safely to the ground. Escape sheet 26 may be constructed in accordance with US Pat. No. 3,525,490 or US Pat. No. 3,542,319, incorporated herein by reference. In any event, the escape seat may include an escape rocket 30 or similar device for propelling the seat out of the aircraft, and includes a first container 32 with a releasable lid containing a parachute and an H-opening mechanism 16. and a deployable container 34 for separately housing the drogue parachute portion of the parachute. In another embodiment, the parachute container 32 may be tied directly to the crew member with a string.

As can be seen in FIG. 5, the parachute 14 includes a plurality of hanging cords 36 and an umbrella 38. These slings 36 are ultimately tied to the aircrew so that once the parachute is fully deployed, the aircrew can leave the escape seat and travel through the parachute to the ground.

A circular opening or vent 40 is located in the center of the top of the umbrella. Air can flow through this vent 40 when the parachute opens and descends in the open position. As can be seen in FIGS. 8 and 9, both ends of the plurality of vent strings 42 are connected to both sides of the sewn edges 44 of the umbrella forming the vent. A strump or pre-ladle 46 is connected to these vent strings at one end and to the disposal device 12 at the other end.

As shown in Figures 5 and 6, the parachute umbrella 3
8 is opened by a fulling device in the form of a ballistic deployment gun operated via a snap cord 50 connected to the escape sheet.

This ballistic gun is manufactured by U.S. Patent No. 3, shown here for reference.
281098. Alternatively, after evacuation of the evacuation seat from the aircraft, the parachute umbrella can be opened solely by the air pressure of the airflow to which it is exposed.

Referring again to FIGS. 3 to 6, the deployment mechanism 16
A first string 52 connected to the disposal device 12 (as also shown in FIGS. 8 and 9), a locket 54 connected to the first string, and a twentieth string 56 connected to the locket. , 20) Drogue or auxiliary parachute 5 connected to a string
8 is shown. The first lace 52 is connected in a conventional manner to a locket 54 which is connected to a retractable hinge pin 5 as seen in FIG.
5 is initially attached to the escape seat in a conventional manner. The drogue parachute 58 can be used to decelerate and stabilize the escape seat immediately after evacuation and to align the rocket before releasing it.

Then, after the seat has decelerated to a predetermined speed, the rocket is disconnected from the escape seat, and the entire deployment mechanism 16 can pull out the parachute 14 from the container 32, as shown in FIGS. 2 to 5. can. This rocket coupling, use of a drogue, and sequence of operations disclosed in US Pat. No. 3,726,499, incorporated herein by reference, is advantageously performed during a low speed escape. In high-speed escapes, the drogue parachute plays an important role in extracting the main parachute.

Deployment mechanism 16 is also used to open the parachute in low speed escapes. It may have a pilot parachute connected to the first string at the stern of the sacrificial device. In this case, the remainder of the deployment mechanism, including the rocket 54 and the larger drogue parachute, may be separated by a pilot parachute, as disclosed in U.S. Pat. No. 3,595,501, incorporated herein by reference. in any case,
The sacrificial device 12 and actuation device 10 according to the present invention can be used with any type of deployment mechanism.

As best seen in Figures 7 to 9, the disposal device 1
2, the latch 60, the housing 62, and the release pin 64;
and a coil spring 66. The latch 60 has a first cylindrical rod 8 with a notch 70 formed at one end, a disc 72 connected laterally to the other end of the first rod, and a disc 72 perpendicular to the disc. and a connected flange 74. The flange 74 has an aperture 76 for receiving the first string of the deployment mechanism, as seen in FIGS. 8 and 9. The first rod has a transverse through hole 78 for receiving a lead shear rivet 80 for shearably connecting the latch 60 to the housing 62, as seen in FIGS. is formed. This rivet shear value is such that it is not sheared when the parachute is pulled out of the container by the deployment mechanism, but is sheared by the force generated by the opening of the main parachute 14. As can be seen in FIG. 9, the main parashade 14 is
The pull of the lanyard moves the housing 62 toward the parachute. Tack tie cords may be used without using rivets.

By making the rivets out of lead, the sacrificial device can be x-ray inspected once the parachute has been packed to ensure proper connection of the sacrificial device. As seen in FIG. 7, the housing 62 has an open end and is hollow, including a first longitudinal cylindrical shape 82 and a second longitudinal cylindrical shape having a diameter smaller than the first hole. It has a through path formed by a shaped hole 84. 20th) The diameter of the hole 84 is slightly larger than the outer diameter of the first gold ring 8. As can be seen in FIG. 8, this rod is slidably received in this hole. The first six 820) diameter is the coil spring 66
The diameter of the receiver is such that it can be slid freely.

A shoulder 86 formed between the coaxial first and twentieth holes is such that when positioning the coil spring 66 within the first hole, as seen in FIGS. One end of the coil spring 66 is received. There are a pair of tightly coupled flanges 88 and 90 on opposite sides of the housing adjacent the first hole. As seen in FIGS. 8 and 9, each of the flanges has holes 92 and 94 for receiving the ends of lanyards 18 and 20, respectively.

As can be seen in FIG. 7, the release pin 64 includes a 20th) rod 96 having a first cylindrical portion and a 20th) cylindrical portion 1 (10), and an eye 1 firmly connected to the first cylindrical portion.
It consists of 02. As can be seen in Figures 8 and 9,
Strap 46 is connected to eye 102 and lanyards 18 and 20 are guided from the sacrificial device toward the parachute by threading through eye 102. The first cylindrical portion 98 is slightly smaller than the diameter of the housing 620) and the first cylindrical bore 820) such that it is slidably received within the bore 820) as shown in FIG. Can be done. 20th) The outer diameter of the cylindrical portion 1 (10) is
20) of the housing, so that the latch 60 is slightly smaller than the inner diameter of the hole 84 in the housing, so that the latch 60 is slightly smaller than the inner diameter of the hole 84 in the housing, as seen in FIGS. 8 and 9. There is a notch 104 that can be engaged with the notch 70 of the first rod 68 . In this interconnected position, the first rod 68 is received in the housing with the disc 72 engaging the end of the housing, and the 20th) cylindrical portion 1 (10) of the release pin is located within the housing and ,
The receiver is placed in the spring 66. This spring engages a shoulder 106 between cylindrical portions 98 and 1 (10) to maintain tension between the housing, latch, and release pin.

Additionally, in this position, the shear rivet 80 extends through the side hole 7 of the first rod 68 through the side hole 108 of the housing.
Uke is accepted at 8.

As can be seen in FIGS. 8 and 9, the actuating device 10 according to the invention comprises a first activation lanyard 18 and a twentieth)
It consists of a starting lanyard 20, a first pulley ring 22, and a 20th) pulley ring 24. These rings are connected to the parachute adjacent diametrically opposite sides of the vent 40 by webbings 110 and 112, respectively. This wesobing has 40 vents.
It is suitably sewn or riveted to the seam edges 44 constituting the .

The first lanyard 18 is connected at one end to the sacrificial device 12 by a flange 88 and at the other end by looping the lanyard around the second ring 24 and attaching it to itself. 20) Connected to ring 24. This first lanyard also passes through a first ring 22. Similarly, the 20th) lanyard 20 is connected at one end to the sacrificial device by a flange 90 and at the other end to the first ring. This 20th) lanyard passes through the 20th) ring. Although it may appear that only one lanyard is required to operate the sacrificial device, two are used as shown in Figures 8 and 9, as their margins and symmetrical loading provide reliability. is advantageous.

Operation In use, the drogue parachute 58 is initially packed into the container 34 supported by an escape sheet. The parachute 14 and the sacrificial device 12 supporting the actuation device 10 are then packed into the other container 32.

As shown in FIGS. 1 and 2, during an evacuation, the container 34 with the drogue parachute 58 is thrown into the air stream, and the drogue parachute is released from the container by the air stream and actuated, thus providing an escape seat. to slow down and stabilize the rod 54, aligning it with the rear of the seat before release.

As shown in FIGS. 3 and 4, after reaching a predetermined low speed, the deploying rocket 54 pulls out the parachute 14 and sacrificial device 12 from the sheet container 32. Next, as shown in FIGS. 5 and 6, the ballistic deployment device 48 is activated by the snap string 50, and the parachute umbrella 38 is activated.
Start opening.

Compare Figures 5 and 6 for the air pressure resulting from the forward velocity of the seat during evacuation from the aircraft after the umbrella begins to open and it receives the initial air, and Figure 8. When compared with Figure 9, the umbrella swells further as shown.
It will spread laterally.

As the deployment mechanism 16 tensions the cord 52, the sacrificial device 12, the strap 46, and the vent cord 42, a force is generated by the lateral expansion of the parachute umbrella 14;
This force is transmitted along the lanyard laterally of the parachute and along the length of the sacrificial device, thus
As shown, housing 62 is pulled downwardly against spring 66 over first cylindrical portion 98 .

When this happens, the stake is 60.1! : The cutout interconnection with the release pin 64 is no longer surrounded by the housing, thus allowing the latch to separate the lock and release pin, as illustrated in FIG. Once this occurs, the deployment mechanism 16 is discarded and separated from the remaining parachute.

As can be seen by comparing FIG. 8 and FIG. 9, the horizontal expansion of the umbrella widens the diameter of the vent 40 in the horizontal direction. For example, because the lanyard 18 is rigidly connected to the housing at one end and to the 20th ring (and thus the parachute) at the other end, the lateral extent of the vents allows the lanyard to Pulling through the first ring 22, which acts as a pulley, the housing moves downwards. 20th) Lanyard 20 and 20th) Ring 2
Similar behavior occurs for 4. 20th) The ring 24 is a pulley in this case.

Thus, actuator 10 separates the deployment mechanism from the parachute by actuating the sacrificial device in response to the parachute opening a predetermined amount. As illustrated in FIGS. 8 and 9, this predetermined amount has sufficient lateral extent to pull the housing 62 downwardly by the lanyard to expose the interlocking notches of the latch and release pin. It is.

Embodiment of FIG. 10 The embodiment of the invention shown in FIG. 10 has four pulley rings 22, 22', 24, 24' instead of two connected to the parachute adjacent the vent 40; It is also similar to the embodiment shown in FIGS. 1-9, except that instead of two, four launching lanyards 18, 18', 20' extend between the housing 62' and the parachute. .

Rings 22 and 24 are diametrically opposed as shown in FIGS. 1-9, and rings 22' and 24' are also diametrically opposed, and these four rings are spaced 90' apart around vent 40. is separated.

The housing 62' accommodates each lanyard 18, 18', 20
．． 20' each have four flanges 88, 88', 90, 90' (not shown) for rigidly connecting them to the housing. The first lanyard 18 and the twentieth) lanyard 20 have rings 22 and 24 if
! and their ends are secured to rings 24 and 22, respectively, as shown in FIGS. 1-9. Similarly, the third lanyard 18' may have one end connected to the housing 62, for example by attaching the lanyard to a loop around a ring.
', and the other end is connected to the fourth ring 24'. This third lanyard likewise has a third ring 22.
′. Similarly, the fourth lanyard 20' is connected to the housing at one end and to the third ring 22' at the other end. This fourth lanyard similarly passes through the fourth ring 24'.

The four rings and four lanyards shown in FIG.
It operates as previously discussed for 8.20. However, the use of four rings and four lanyards, each in diametrically opposed pairs, increases the system's headroom and prevents the parachute from becoming loose in the event that one ring becomes dislodged from the parachute. Avoid single point breakage that may occur in embodiments. Furthermore, the ring is 90°
The use of four spaced rings and four lanyards provides a more balanced pulling force on the housing.

Although one advantageous embodiment has been chosen to illustrate the invention, those skilled in the art will appreciate that various changes can be made without departing from the scope of the invention as specified in the appended claims. You will understand what you can do.

[Brief explanation of the drawing]

FIG. 1 is a schematic side elevational view of the aircrew in the ejector seat beginning to eject from the aircraft and the container of the drogue parachute being thrown from the ejector seat. FIG. 2 is a schematic side elevation view similar to that shown in FIG. 1, except that the deployment rocket releasably connected to the seat and drogue parachute has been pivoted away from the seat; Figure 3 is a schematic side elevation view similar to that shown in Figure 2, except that the deployment rocket has left the seat and the main parachute has exited the seat container due to the interaction of the rocket and drogue parachute. Figure 4 is a schematic side elevation view similar to that shown in Figure 3 except that the parachute has been fully retracted from the container of Sea 1-. Figure 5 is an enlarged view. Figure 6 is a schematic side elevation view similar to the view shown in Figure 4, except that the parachute has opened further and the deployment gun has begun to open the parachute; 7 is a schematic side elevational view similar to that shown in FIG. 5, except that the deployment mechanism is discarded from the parachute by activation of the discarding device. FIG. FIG. 8 is an enlarged exploded side elevational cross-sectional view of parts showing details of the disposal device shown in FIGS. 8 and 9. FIG. The actuating device according to the invention is shown in more detail,
FIG. 3 is an enlarged exploded side elevational sectional view of the component. FIG. 9 is similar to the view shown in FIG. 8, except that the parachute opens a predetermined amount, as illustrated in FIG. 6, thereby activating the sacrificial device and separating the deployment mechanism from the parachute. FIG. 2 is a schematic side elevational view. FIG. 10 is an inverted view of a modification of the invention similar to that shown in FIGS. 8 and 9, except that four pulley rings and four activation lanyards are used. 10... Actuation device 12... Disposal device 14...
Parachute 18.18', 20.20'...Laniard 22.22'24.24'...Ring
26... Escape seat 28... Crew 29
...Aircraft 30...Escape rocket 32.3
4...Container 36...Hanging string 38...Umbrella body
40...Vent 42...Vent string 44
...Sewn edge 46...Strap 48...Ballistic deployment gun 50...Snap string 52.56...
String 54...Rocket 55...Hinge pin
60...Latch is metal 62.62'...Housing 64...Release pin 66...Coil spring
68.96...Rod 70.104...Notch 72...Disc 74...Flange 76...
Hole 78.108... Horizontal hole 80... Shear rivet 82, 84... Cylindrical hole 88.
88', 90.90'...Flange 92.94.
...hole 98.1. OO...Cylindrical part 102...
・Eye 106... Shoulder 110.112... Sea urchin rubbing μ

Claims (1)

[Scope of Claims] (1) A parachute deployment device including a parachute packed in a container, a deployment mechanism for pulling out the parachute from the container, and a disposal device for discarding the deployment mechanism from the parachute, comprising: a parachute and a disposal device; What is claimed is: 1. A parachute deployment device, comprising a device connected to the parachute and configured to operate a sacrificial device in response to opening of the parachute by a predetermined amount. (2) the device comprises first and second spaced rings connected to the parachute adjacent the top of the parachute; one end connected to the sacrificial device and the other end connected to the parachute; a first lanyard connected to a second ring and passing through the first ring; one end connected to a sacrificial device and the other end connected to the first ring and passing the second ring; The parachute deployment device according to claim 1, further comprising a second lanyard passing through the parachute deployment device. (3) The parachute has a vent at its top, and the first ring and the second ring are arranged adjacent to the vent. Parachute deployment device described in paragraph ). (4) The vent hole is substantially circular, and the first ring and the second ring are disposed on diametrically opposite sides of the circular vent hole. Parachute deployment device according to scope item (3). (5) a guide device coupled to a disposal device for guiding the first lanyard and the second lanyard toward the first ring and the second ring, respectively; A parachute deployment device according to claim (2). (6) The actuating device includes a device for transmitting force generated by the lateral expansion of the parachute to the device.
Parachute deployment device described in paragraph ). (7) the device includes a ring connected to the parachute adjacent to the top of the parachute; and a lanyard connected at one end to the sacrificial device and at the other end to the parachute, the lanyard being connected to the parachute The parachute deployment device according to claim 1, wherein the parachute deployment device passes through a ring. (8) the parachute has a vent at its top, said ring being positioned adjacent to one side of said vent, and the other end of said lanyard being adjacent to the other side of said vent to the parachute; A parachute deployment device according to claim 7, characterized in that the parachute deployment device is connected to a parachute deployment device. (9) A device for discarding a parachute deployment mechanism for pulling out a parachute from a container, the device being connected to a deployment device for pulling a parachute out of a container, and a parachute and the deployment mechanism, and releasing the parachute and the deployment mechanism. a sacrificial device coupled to the sacrificial device and the parachute for activating the sacrificial device to release the connection between the parachute and the deployment device in response to opening of the parachute by a predetermined amount; and an actuating device. (10) The disposable device according to claim (9), wherein the deployment device includes an auxiliary parachute. (11) The disposable device according to claim (10), wherein the deployment device further includes a rocket. (12) The disposal device according to claim (9), wherein the deployment device includes a rocket. (13) The disposal device includes a first rod having a first notch at one end and connected to the deployment device at the other end, and a second notch at one end. and a second rod whose other end is connected to the parachute, the first notch and the second notch being connected to the first
and the second rod can be engaged to interconnect the first rod and the second rod when the first rod and the second rod are interconnected. Disposal device according to claim 9, characterized in that it includes a surrounding hollow housing with an open end. (14) The actuation device includes a ring connected to the parachute adjacent to the top of the parachute, and a lanyard connected to the housing at one end and connected to the parachute at the other end, the lanyard being connected to the parachute at one end. The disposal device according to claim 13, characterized in that the disposal device passes through the ring. (15) the parachute has a vent at the top thereof, the ring is disposed adjacent to one side of the vent, and the other end of the lanyard is adjacent to the other side of the vent to the parachute; A disposal device according to claim 14, characterized in that the disposal device is connected to. (16) The actuation device includes a ring connected to the parachute adjacent to the top of the parachute, and a lanyard connected to the housing at one end and connected to the parachute at the other end, the lanyard being connected to the parachute at one end. The disposal device according to claim 9, characterized in that the disposal device passes through the ring. (17) the parachute has a vent at its top, the ring being disposed adjacent to one side of the vent, and the other end of the lanyard being adjacent to the other side of the vent; A disposal device according to claim 16, characterized in that the disposal device is connected to. (18) The actuating device includes a device for transmitting force generated by the lateral expansion of the parachute to the dissipation device.
9) A sacrificial device (19) comprising four rings connected to the parachute adjacent the top of the parachute, and four lanyards, each lanyard connected at one end to the sacrificial device and at the other end. A sacrificial device according to claim 9, characterized in that the ends of the parachute are connected to the parachute and pass through different ones of the four rings. (20) A method of deploying a parachute from a container and discarding the deployment mechanism from the parachute, which includes a stage of pulling the parachute from the container by the deployment mechanism, a stage of starting to open the parachute, and a stage of deploying the parachute by a predetermined amount according to the opening of the parachute. separating the mechanism from the parachute. (21) The method for disposing of a deployment mechanism according to claim (20), wherein the step of separating involves separating the deployment mechanism from the parachute by using force generated by opening the parachute. . (22) A method for discarding a deployment mechanism according to claim (20), comprising the step of separating the deployment mechanism from the parachute by transmitting a force generated by the lateral expansion of the parachute.