Deployment sequencer

[Detailed Description of the Invention]

The present invention relates to the improved control device which controls the deployment of the parachute in the ejected type seat of an airplane. Although the operation of fundamental operation and its various parts is known quite [ now ] well by the ejection device, there is the method of being variously different for solution of the problem. In the system of one form, a circle lid is removed, a seat and a crew member begin to be recommended from the opening of a circle lid out of an airplane, a parachute opens, and it drops a crew member safely to the ground. In other systems, although the capsule which encloses a crew member is used or other art is used, these are not related to the present invention. The peculiar problem in the ejection and deployment which are well known to a person skilled in the art, It is determining the state which the deployment of the after-ejection parachute can be carried out in order to secure safety rationally to determining a posture and a crew member, or must carry out deployment, or its time in the speed of the seat at the time of ejection, an altitude, and a certain case. When speed is not much large, when a parachute opens, a parachute may break, or a crew member may experience a shock of a slowdown of the degree of excessiveness, or there is possibility of the both. These problems and problems, and measures against other are explained to the following United States patent. U.S. Pat. No. 2505869 Quilter The 2693326th item Lobelle The 2699305th item Turner etc. The 3067973rd item Halsey etc. The 3311330th item Hofferberth etc. The 3352518th item Turner etc. The 3355127th item Stanley etc. The 3421720th item MacDonald, Jr., etc. The 3547383rd item Carpenter, Jr. The 3669388th item Van Kreuningen The 3726499th item Stencel The 3862731st item McIntyre The 4057206th item Duncan etc. Although some of art indicated by these articles can be used satisfactorily, there is a problem in the accuracy of measurement of some problems of Leave it especially the reliability of a control device, and airspeed. It is intermediary To have with that different degree of complexity by the design method by which an electronic circuit device is used for the control device generally called the "sequencer" (sequencer), and this circuit device is used. these control circuits are electromagnetic -- receiving disturbance by "a noise, i.e., the surrounding radio and radar transmission without the direct relation to this system," -- I or intermediary To have. For example, when the airplane "has immersed" into the radio from the control tower or aviation Mother's book of the field where an airplane lands, or a radar signal, the control device may not operate correctly. A problem is Oh for determining the optimal time of the deployment of a parachute, and a seat / crew member separation arising aside from an airplane, since the feature of movement of a seat and a crew member is difficult to expect correctly. The object of the present invention, or the object of the example of at least the following present invention, It is providing the deployment control device of the advanced parachute by which the reliability on operation has been improved, and is providing the deployment control device of the parachute by which the determination of airspeed is improved and the deployment of the parachute was attained by it in the suitable environment. In the sequence device which controls the deployment of the parachute by which the present invention will follow ejection of the seat from an airplane if explaining it briefly, The initiator attached to the seat in order to carry out deployment of the parachute, the left Pitot tube and the right Pitot tube which were attached to the seat, The housing attached to the seat, the 1st in this housing, the 2nd, and the 3rd, It is arranged in the bellows which takes the state where it elongated with the state where operated with air and it contracted, and the above-mentioned housing, The 1st which has connected the contact operation member to the above-mentioned 1st, the 2nd, and the 3rd bellows, the 2nd, and the 3rd switch, A battery, the above 1st, the 2nd, and the point of contact of the 3rd switch are connected mutually in series, And the circuit which connects the point of contact of the above-mentioned switch to an above-mentioned battery and initiator, The 1st lead pipe that applies ambient air pressure to the 1st above-mentioned bellows so that the point of contact of the switch combined with the 1st above-mentioned bellows may close below at a predetermined altitude, And it has the above 2nd, the 2nd which apply automatic style pressure to the above-mentioned 2nd and the 3rd bellows to the 3rd bellows, and the 3rd lead pipe from the Pitot tube of the above-mentioned left and right so that a switch may be closed, when the pressure the Pitot tube of the above-mentioned left and right is pressured expresses the airspeed below predetermined airspeed, If the above 1st, the 2nd, and all the 3rd switch close by that cause, the sequence device which controls the deployment of the parachute operating the above-mentioned initiator and making a parachute open is provided. The operation type thermal cell which formed the pistol which answers ejection of a seat and operates a battery may be sufficient as the above-mentioned battery. The above-mentioned housing is also substantially continuous lead pipe Ciel which constitutes electromagnetic shielding. With reference to drawings, the example of the present invention is described below. Drawing 1 shows the typical crew member seat part containing the seat which can eject the form which can apply the present invention. Including the ejection seat which, on the whole, shows the device illustrated on the drawing in order to show the environment and common equipment which can use the present invention by 10, this has a parachute in parachute container 11, and has a streamer in blow-off container 12. The upper end of a seat has circle lid penetration device 13, and the seat had propulsive engine 14 which promotes a seat from a cockpit, this seat is provided with the runner, and this runner can carry out a Along run at rail 16 which remains in an airplane after seat ejection. Since the ejection mechanism itself containing the automatic contrivance for removing the container at a special parachute container and the suitable time is not related to the present invention, explanation is not given any more. The thing of various form can be used for these devices. The important things especially for the present invention are two things which can be arranged in zone 17 between a back base material and a seat seat part and which were substantially established for the isomorphous metal housing. The important thing in Drawing 1 is having provided manual handle 18 which can operate an ejection mechanism. It separates from a seat structure, and where a metal cover is removed, the housing is shown in Drawing 2. As shown in Drawing 2, two housings 20 and 21 are substantially the same. Each housing is a metal container and is continuing substantially except for the portion of the opening for introduction of a various lead pipe and other devices. In this way, each housing forms the very effective shield which prevents electromagnetic interference which arises with a surrounding radar and radio signal, and prevents the electronic device in a housing from being affected with the above signals. Housings 20 and 21 have stored the same device. Therefore, only the device in housing 20 is explained. It will be understood that the device in housing 21 is a thing with the same structure and function. Housing 20 can generate 10 v of voltage [ 35 v of ] between DC(s) with DC, and contains thermal cell 22 which can give a minimum of 6-A current to 1 ohm of resistance load. When a thermal cell is also called a synthetic electrolysis battery (fused-electrolyte battery) and heat operation battery (heat activated battery), connects many bimetal junction and is heated, it is a battery which produces voltage. The thermal cell of this form does not give an output until that operation is started artificially. If operation is started, the time for 300 seconds and output voltage will arise after the delay for about 0.025 second. Activation of a battery is started by igniting a pistol or percussion percussion cap 23, and this ignition is attained by firing pin 24. Movement of a firing pin is made to arise with the gas pressure in lead pipe 25 from pressure A tap on the catapult (not shown) itself. If ejection of a seat is made in this way, the gas supplied through lead pipe 25 will start operation of a battery. Housing 20 includes the 1st switch 28, the 2nd switch 27, and the 3rd switch 29 which were sealed, and these points of contact have between an opened state and closed states, as for each switch, moved by motion of contact operation members 30, 31, and 32 of the form of a stick including Point of Always open. These contact operation members are connected with the 1st bellows 36, the 2nd bellows 35, and the 3rd bellows 37. As for the 2nd bellows 35, lead pipe 39 and the 3rd bellows 37 are connected to lead pipe 40. These lead pipes are connected to Pitot tube 41 of the left and the right which are attached to the both sides of parachute container 11. Even if Pitot tube 41 used is shifted about 45 degrees to the air current, it is a keel (Kell) type Pitot tube which answers all the pressure heads correctly. In this way, the 2nd bellows 35 and 3rd bellows 37 operate with the total freedom style pressure which is the dynamic pressure measured by the air current which passes along a Pitot tube on either side. Bellows 35, 36, and 37 move between the states where it elongated with the state where it contracted, and act on contact operation members 30, 31, and 32. The 1st bellows 36 answers the pressure by which it has opened wide to ambient pressure via the 1st lead pipe 42, therefore denotes an altitude. It can Set as switch 27 or 29 is opened when the airspeed of the seat after ejection is more than 325KEAS (knots equivalent airspeed), and switch 28 is open when an altitude is more than a pressure altitude of 14000 feet (4200 m) and. The switch has been opened until speed or an altitude fell to below these preselected numbers. Other speed and advanced parameters can also be chosen so that it may understand here, but these values are chosen as what expresses with more than it speed and the high speed that the deployment of the parachute cannot be carried out safely. Here, the conventional Escape system is set after ejection beyond the critical value (typically 200KEAS thru/or 300KEAS) of a certain airspeed, It must be cautious of the same thing as the time needed by ejection of 600KEAS done for "bias" so that deployment may not be carried out to not carrying out time progress. This gives extreme time disadvantage from the above-mentioned critical speed to the ejection which arises on small. The point of contact of switches 27, 28, and 29 is connected in series, as seen in the outline circuit diagram of Drawing 3. As other elements shown in Drawing 3, there are various circuit elements provided on battery 22 and circuit board 43 and explosion bridge wire initiator 44. This initiator 44 is connected to two TLX (thinlayer explosives, thin Layer explosive charge) transmission lines 45. A TLX line comprises what enclosed the flexible plastic pipe with the protective cover of Braid stainless steel. This pipe has the reaction material (train material) pushed out by the inside at one, and if this is lit by one end, it will carry a signal to the other end certainly from one end. The speed of a signal is 6500 feet (1950 m) / second. A TLX line is lit by a pistol initiator, a bridge wire initiator, or other TLX lines at one of ends. However, this is not lit by being exposed to the state of a flame and other unexpected occurrences which may arise within an airplane. The TLX line shown in Drawing 2 was extended to the trunk deterrence mechanism usually established on the ejection seat, in order to hold a crew member firmly on a seat, and it is extended to cover Release of streamer container 12 and parachute container 11. In the circuit shown in Drawing 3, battery 22 has two parallel lamination batteries, and these are connected in parallel with diodes 46 and 47. These diodes are connected to the end of the series circuit containing the point of contact of switches 27, 28, and 29, and fixed resistance 48 is provided in parallel with this circuit. The other end of this series parallel circuit is connected to resistance 51 which is connected to SCR50 and makes a part of in-series RC circuit. Other portions of this RC circuit are capacitors 52. The spot weld of resistance and a capacitor is connected to the gate of SCR50 via Diack 53. The output of SCR50 is connected to bridge wire initiator 44. RC circuit containing resistance 51 and capacitor 52 gives the delay of a short time for about 0.050 second. This builds the delay for a total of 0.075 second, before the activation of To join and a circuit to the start delay of the thermal cell for 0.025 second. Since resistance 48 is provided in an in-series switch circuit and Flat line, the time delay of RC is usually ended, before the closed way of the switch 27-29 is carried out. In this way, after 0.075 second passes since operation of a catapult, and ejection of a seat, a sequence control device lights explosion bridge wire initiator 44, shortly after three switches of the closed way of all are done. Also in this case, an initiator puts various TLX transmission lines into operation, and starts the operation after ejection called Release of a deterrence object, Release of a streamer, and opening of a parachute container. Here, please recognize that the sequence control device contains the excessive thing on the whole. Intermediary To have [ as ] which each of two housings 20 and 21 has a device which can carry out deployment, and a pressure impulse and a Pitot tube input for each of a housing to activate the battery are supplied, and operates a bellows in parallel. Each unit is small, it is compact, all the electric elements that receive electromagnetic interference are put in the shielded box, and sufficient reliability is acquired. In order to explain the present invention here, the suitable example was chosen as it, but it will be understood by the person skilled in the art that versatility can be transformed, without deviating from the technical scope of the present invention.

[Brief Description of the Drawings]

The outline side view showing the airplane seat of form in which Drawing 1 can apply the present invention, the upper surface figure where Drawing 2 made the section some sequence control devices by the present invention, and Drawing 3 are outline circuit diagrams of an operation circuit usable to the device of Drawing 2. 10 ...... An ejection seat, 11 ...... A parachute container, 12 ...... A streamer container, 13 ...... A circle lid penetration device, 14 ...... A propulsive engine, 16 ...... A rail, 17 ...... A housing zone, 18 ...... A handle, 20, 21 ...... A housing, 22 ...... A thermal cell, 23 ...... A percussion percussion cap, 24 ...... A firing pin, 25 ...... A lead pipe, 27, 28, 29 ...... A switch, 30, 31, 32 ...... An operation member, 35, 36, 37 ...... A bellows, 39, 40 ...... A lead pipe, 43 ...... [ ...... A diode, 48 / ...... Fixed resistance, 50 / ...... SCR, 51 / ...... Resistance, 52 / ...... A capacitor, 53 / ...... Diack. ] A circuit board, 44 ...... An initiator, 45 ...... A TLX transmission line, 46, 47