WO1992010403A1 - Sicherheitseinrichtung für ein drehflügelflugzeug - Google Patents
Sicherheitseinrichtung für ein drehflügelflugzeug Download PDFInfo
- Publication number
- WO1992010403A1 WO1992010403A1 PCT/AT1991/000125 AT9100125W WO9210403A1 WO 1992010403 A1 WO1992010403 A1 WO 1992010403A1 AT 9100125 W AT9100125 W AT 9100125W WO 9210403 A1 WO9210403 A1 WO 9210403A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- rotor shaft
- rotor
- wing aircraft
- rotary wing
- safety device
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/006—Safety devices
Definitions
- the invention relates to a safety device for a rotary wing aircraft with at least one rotor which can be driven via a central shaft, which rotor shaft penetrates the cell roof of the rotary wing aircraft.
- Such a safety device was known from DE-OS 36 17 294.
- the rotor shaft is hollow, a parachute being accommodated in this cavity, which is large enough to brake the rotary-wing aircraft in the event of a crash to a safe sinking speed.
- this solution is only suitable for small rotary wing aircraft, if at all, since only parachutes up to a certain size can be accommodated in the rotor shaft.
- the aim of the invention is to avoid these disadvantages and to propose a device of the type mentioned at the beginning which offers a high degree of safety for the crew of a rotary wing aircraft in the event of a crash.
- the rotor shaft is subdivided, the two parts being connected to one another in a rotationally fixed manner and an activatable explosive device being arranged between these parts and a further explosive device for detaching an ejection seat or cockpit, which is provided according to the Activation of the explosive device arranged at the connection point of the rotor shaft can be activated.
- the part which is connected to the cell roof in a rotationally fixed manner and penetrated by the rotor shaft is held in the cell roof so that it can be pulled out upwards and is provided with a propellant charge with a short burning time which acts in the longitudinal direction of the rotary wing aircraft Has beam direction and which can be activated with a short delay after the activation of the explosive device assigned to the rotor shaft.
- At least two propellant charges are arranged on the part of the rotor shaft connected to the rotor, the propellant charges being arranged uniformly on the circumference of the rotor shaft, the jet directions of which are directed tangentially to the rotor shaft against the direction of rotation of the rotor shaft and which are simultaneous however, it can be activated with a slight delay compared to the propellant charge acting on the rotor shaft in the longitudinal direction of the rotary wing aircraft.
- a brake parachute can be accommodated in the part of the rotor shaft blasted off with the rotor, which can be ejected after a certain time after the blasting off of the rotor. Since this expediently takes place after the rotor has been braked, there are hardly any significant problems. In addition, failure of such a parachute does not endanger the crew of the rotary wing aircraft.
- Fig. 1 schematically shows a part of the rotor shaft
- Fig. 2 schematically shows a trigger circuit for an explosive or propellant charge.
- the rotor shaft 1 is subdivided, the two parts 2 and 3 engaging via a non-circular central pin 4 on the end face which engages in an opposite end recess 5 of the second part 3 of the rotor shaft 1.
- the two parts 2 and 3 are held together by a bracket-like part 6.
- an explosive charge 7 is arranged in the recess 5, which can be triggered by the crew, with the triggering of this explosive charge 7 starting a timer, not shown, after the expiration of which another explosive charge, not shown, is ignited by one Eject the ejection seat after the cabin roof has blown off.
- a ring part 9 is held non-rotatably in the cell roof 8 via struts 10 which can be pulled out of the cell roof 8.
- a propellant charge 11 is held in this ring part 9, the jet direction of which runs in the longitudinal direction of the rotary-wing aircraft.
- a bearing ring 12 is also held on these struts 10.
- a control 13 is arranged in this, which is set when the explosive charge 7 is triggered and is activated when the lines 14 are interrupted. This leads to an ignition of the propellant charge 11 via the line 15 and, after a short delay, also to the simultaneous ignition of the two propellant charges 17 arranged on the part 3 of the rotor shaft 1 connected to the rotor 16. These two tangentially at opposite points The propellant charges 17 arranged in the rotor shaft 1 have a jet direction opposite to the direction of rotation of the rotor shaft, so that after their ignition they act in the sense of braking the rotor shaft.
- the ring part 9 serves primarily as a platform for the propellant charge 11, it also being possible, if appropriate, for an existing landing parachute for the rotor to be attached to this part.
- the ring part 9 is mounted around the rotor shaft in such a way that it can be displaced along the shaft and does not hinder the rejection of the rotor.
- the ring part 9 is located between the cell roof 8 and a bearing ring 12, so that the ring part 9 is in this state is immobile.
- the bearing ring 12 is also fixed by the bearing on the rotor shaft.
- the ring part 9 When the rotor is blown off together with the upper part of the shaft on which the bearing ring g 12 is mounted, the ring part 9 is pulled along by brackets at the lower ends of the extendable struts 10.
- the ring part 9 can also be connected to the cell roof 8 by predetermined breaking points. A stable mounting of the ring part 9, which could be a hindrance when the rotor is blown off, is avoided by the bearing ring 12. Since the lower ends of the struts 10 are at the same height as the lower end of the blown-off part of the rotor shaft, it is ensured that the ring part 9 as the basis of the propellant charge 11 is located at the lowest end of the blown-off shaft part.
- the voltage supply to the controller 13 is maintained by a memory arranged in the controller, preferably a capacitor.
- the propellant charges 17 are supplied with a corresponding ignition pulse by means of insulated conductive pads arranged at corresponding locations on the rotor shaft 1, which are supplied via a corresponding slip ring 18.
- the explosive charge 7 is ignited via a line (not shown) and the control is set at the same time.
- the former leads to the part 3 of the rotor shaft 1 being blown away, the clip-like part 6 being bent away or the flange 19 of the part 3 of the rotor shaft 1 being sheared off.
- the ring part 9 and the bearing ring 12 are also moved upward away from the cell roof 8, the struts 10 being pulled out and the line 14 tearing.
- the latter activates the control 13, which ignites the propellant charge 11, as a result of which the rotor 16 and the rotor shaft tip sideways due to the precession.
- the ejection seat (not shown) is activated and is removed from the rotary wing blown away, whereupon the crew can jump off with a parachute.
- Fig. 2 shows schematically the control 13. This is only connected to the electrical system by activating the rescue system, e.g. when the ignition knee is fired to ignite the propellant to blow off the rotor shaft. In the normal flight state, the controller 13 is therefore not connected to the vehicle electrical system and therefore remains deactivated.
- the controller 13 has a capacitor C1 which is charged when the controller is connected to the vehicle electrical system. Discharge of this capacitor is prevented by the two diodes D1 and D2.
- the integrated circuits IC1 and IC2 are integrated with the connections IC1-4 and IC2-1 in the circuit, while they are connected with the connections IC1-2 and IC2-8. Via IC-5 they receive a switching signal for IC1- 2, which blocks the IC2-9 connection.
- the switching signal from the connection IC1-5 drops below a predetermined threshold voltage, the IC circuit being retained by a current limited via the resistor R2 and IC2-9 sending a signal current to the Gateelek ⁇ trode of the thyristor Thl delivers.
- the thyristor Thl now closes the circuit to the gate electrode of the thyristor Th2, the control resistor R4 being used to adjust the control current for the thyristor Th2.
- the capacitor C1 is discharged via the thyristor Th2 via the consumer X and the resistor R3 connected in parallel therewith, the discharge time being determined by the resistor R3.
- the consumer X is e.g. a filament that serves as a primer for a propellant charge.
- a rotor that can be driven via a central shaft is provided.
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AT250390A AT396676B (de) | 1990-12-10 | 1990-12-10 | Sicherheitseinrichtung für ein drehflügelflugzeug |
ATA2503/90 | 1990-12-10 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1992010403A1 true WO1992010403A1 (de) | 1992-06-25 |
Family
ID=3535451
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/AT1991/000125 WO1992010403A1 (de) | 1990-12-10 | 1991-12-06 | Sicherheitseinrichtung für ein drehflügelflugzeug |
Country Status (3)
Country | Link |
---|---|
AT (1) | AT396676B (de) |
AU (1) | AU8933691A (de) |
WO (1) | WO1992010403A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19820323A1 (de) * | 1998-05-07 | 1999-11-11 | Werner Uhrmann | Rettungssystem für Hubschrauber-Besatzungen mit Abtrennung der Haupt-Rotorblätter |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3229931A (en) * | 1964-07-20 | 1966-01-18 | Agnew E Larsen | Emergency removal of aircraft sustaining means |
US3352513A (en) * | 1966-03-25 | 1967-11-14 | George W Baker | Helicopter rotor shaft and rotor blade severing means |
-
1990
- 1990-12-10 AT AT250390A patent/AT396676B/de not_active IP Right Cessation
-
1991
- 1991-12-06 WO PCT/AT1991/000125 patent/WO1992010403A1/de active Application Filing
- 1991-12-06 AU AU89336/91A patent/AU8933691A/en not_active Abandoned
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3229931A (en) * | 1964-07-20 | 1966-01-18 | Agnew E Larsen | Emergency removal of aircraft sustaining means |
US3352513A (en) * | 1966-03-25 | 1967-11-14 | George W Baker | Helicopter rotor shaft and rotor blade severing means |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19820323A1 (de) * | 1998-05-07 | 1999-11-11 | Werner Uhrmann | Rettungssystem für Hubschrauber-Besatzungen mit Abtrennung der Haupt-Rotorblätter |
Also Published As
Publication number | Publication date |
---|---|
ATA250390A (de) | 1993-03-15 |
AU8933691A (en) | 1992-07-08 |
AT396676B (de) | 1993-11-25 |
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