RU2310585C2 - Two-mode life-saving parachute for ejection seat - Google Patents

Abstract

FIELD: aeronautical engineering.

SUBSTANCE: proposed parachute is additionally provided with system for change of mode of its operation which includes reefing ring mounted on parachute canopy, two pyro-cutters fitted on reefing ring, two unreefing tapes and pyro-lock fitted on head-rest of ejection seat. Upper ends of reefing tapes are secured to pyro-lock and lower ends of these tapes are secured to parachute canopy.

EFFECT: improved characteristics of parachute canopy development at low speeds lesser than 400 km/h.

2 dwg

Description

Known parachutes used on ejection seats (KK) to ensure the landing of the pilot at an acceptable speed, for example parachutes such as AIM, GQ 1000, GQ 5000 firm Irwin Industries, used on the "Western" type ACES-II, SIVS or MK-10, MK -16, and parachutes of the PL-63, PL-81 type used on Russian spacecraft of the K-36D, K-36D-3,5 type and consisting of a dome, slings and free ends with their attachment points to the pilot's suspension system (see “Aircraft crew rescue equipment”, Mechanical Engineering Publishing House, 1975).

Western developers use parachutes with a maximum speed of about 350-400 km / h. Therefore, if the bailout occurs at high speeds, then the parachute is introduced either with a delay that ensures the braking of the spacecraft to the specified speed, or the parachute is introduced immediately, but with a sharpened lower edge, which prevents it from filling at high speed. The lower edge is broken by a pyro-cutter only after a certain time after insertion, for example, after 1.15 s at the ACES-II chair.

According to world statistics, more than 90% of all ejections at low altitudes occur at a flight speed of v≤650 km / h. Since from the point of view of reducing the minimum safe altitude for leaving the aircraft, the process of entering and filling the parachute should be accelerated, Russian developers of parachutes sought to create parachutes with a maximum speed of 650 km / h (PL-63, PL-81). Moreover, at the indicated speed, the maximum allowable levels of exposure to the pilot of overload braking in the process of filling the parachute are realized.

It is quite natural that when you enter this parachute at lower speeds, the magnitude of the overloads and the rate of their growth is significantly less than physiologically permissible. And if it were possible to intensify its filling at low speeds so that the exposure levels were at the level of acceptable, then in this case it would be possible to reduce the time of filling the parachute and, accordingly, reduce the value of the minimum allowable height of departure of the aircraft in an emergency at low speeds. Thus, the task is to, while retaining the unique characteristics of the parachute at high speeds, improve its filling characteristics at low speeds.

To ensure more intensive filling at low speeds, the rescue parachute (see Fig. 1), containing a dome (1), slings (2), free ends (3) with their attachment points to the suspension system, additionally contains a system for changing the mode of operation of the parachute ( SIRP), located on the dome and allowing to intensify its filling at low speed.

SIRP consists of a riffing ring (4) made of a cord fixed on the dome at a certain distance from its lower edge, 2 pyro cutters (5) located on the riffing ring, 2 ribbing tapes (6) attached to the pyrozam lock ( 7) located on the heading (8) of the spacecraft, in which the rescue parachute is placed.

The system operates as follows.

When bailout, using information about the flight speed of the aircraft at the time of the accident, the QC control system submits or does not submit an electric command to the pyro lock (7).

If the speed of the aircraft at the moment of ejection is more than 400 km / h, then the electric command is not supplied to the pyro lock and the lock remains closed. Therefore, when you enter the parachute after pulling the lines, the ribbons are pulled and tear the riff ring. The parachute is filled as usual (see FIG. 1), the sequence of filling steps in this case is shown in FIG. 1a, 1b, 1c, 1d.

If the speed is less than or equal to 400 km / h, with the help of the electric control system developed by the control system of the CC, the pry-locks for fastening the stripping ribbons are opened and in this case the integrity of the ripping ring is preserved, which will be destroyed after a certain time only after the operation of any of the 2 pyro-cutters installed on this ring.

Therefore, at the initial stage, the entire canopy of the parachute will not be filled entirely, but only part of it. Part of the dome is filled more intensively, as a result of which the pilot decelerates more intensively and, accordingly, the loss of altitude is less. And only after a certain time, when either of the two pyrorezak triggers and the riffling ring breaks down, the filling of the entire dome will begin (see Fig. 2), the sequence of steps for filling the parachute in this case is shown in Figs. 2a, 2b, 2c, 2d.

Claims (1)

A bimodal rescue parachute of an ejection seat containing a canopy, slings, free ends with attachment points to the suspension system, characterized in that it further comprises a system for changing the mode of operation of the parachute, which makes it possible to intensify its filling at low speeds and consisting of a reefing ring mounted on the canopy a certain distance from its lower edge, two pyro-cutters mounted on the reefing ring, two stripping ribbons, a pyrozam lock mounted on the head of the said armchair a and openable generated by the control system of said electric command chair, to which are fixed the upper ends razrifovochnyh tapes, and the lower ends of suture are attached to the canopy, the lower end of one of the strips ensures the integrity razrifovochnyh rifovochnogo ring and its attachment to the dome.

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