RU2123458C1 - Flying vehicle spin-recovery system - Google Patents

Abstract

FIELD: aeronautical engineering; on-board parachute-type anti-spin systems. SUBSTANCE: spin-recovery system includes container made in form of tube and mounted in parallel relative to tail section of fuselage; it is provided with parachute device and cargo jettisoning mechanism. Container provided with front and tail fairings and open end is mounted on external store by means of attachment units. Pyrotechnic mechanism closed by tail fairing is located on the container outside on its upper tail section at its outlet end. Jettisoned weight of pyrotechnic mechanism is connected with pilot parachute cover through connecting link of parachute device. Pinned link is secured on the container outside under the same fairing. In center portion of container there is longitudinal guide passage of rectangular section where adapter device is arranged. Adapter device consists of two members interconnected by means of shear stud: one member is connected with link of main parachute and other member is connected with load-bearing attachment unit through additional shorter link of parachute device. Two pyro cutters are mounted inside container in its front portion on vertical longitudinal wall; they are mounted in succession in detachable clips. Above-mentioned additional shorter load-bearing link of parachute is passed through these cutters. Beside that, wall of container is provided with upper hole and side auxiliary holes closed by easily detachable covers. EFFECT: simplification of construction and ease in maintenance; enhanced operational reliability. 3 dwg

Description

 The present invention relates to the field of aviation, and more specifically to on-board anti-cork parachute installations of aircraft and is intended to withdraw the aircraft from the corkscrew or to prevent it from entering the corkscrew during flight tests at large angles of attack, and can also be used as a brake system to reduce mileage after landing and in other cases of a similar property.

 A rescue device for an aircraft is known (see the GDR patent, class 62c22 / B 64 D 17/72 / N 95328, application form 20.03.72, published January 20, 73 g), containing a cylindrical container for storing a folded parachute and placing pyro charges providing the ejection and disclosure of the parachute. The container is mounted on a tubular base, which is mounted by a flange to the power elements of the upper part of the fuselage of the aircraft above the center of mass.

 The same tubular base is the axis for the hollow sleeve, driven into rotation through the bevel gear transmission of the power transmission.

 This design is not reliable enough, not autonomous and complicated.

 The closest analogue of the invention is a device for providing a soft landing of the aircraft (Japanese patent, N 47-20335, 06/09/72, application 42-64467 from 10/06/67 IPC 6 B 64 D 25/00), which contains a container for a parachute made in the form of a cylindrical pipe mounted on the body of the aircraft parallel to its axis. The container has a removable lid, which under normal flight conditions is mounted on the container using a device that prevents the lid from being separated under the pressure of external forces arising in flight. The device contains a detachable head, the front end of which is made in the form of a cone, and the rear is pivotally connected to the casing. The conical cover forms the front fairing of the container.

 A parachute is placed in the container, as well as slings for hanging the aircraft to the parachute when it is opened during an accident. The device also includes a cap securing the head. In the center of the front of the container and its head, a longitudinal rod extends, attached by the front end to the safety cap. A support element is installed in the container, on which the rear end of the rod rests, and a spring support is mounted on the protruding rear part of the rod. A spring is installed between the support element and the support, which in the normal position pushes the rod back and thereby, with the help of the cap, protects the head from opening.

 The intermediate part of the rod is connected to one end of the lever. The opposite end of said lever is connected by means of another lever to a command device located in the aircraft body. The lever has a support around which it can turn. When moving the command device, the lever moves forward in the casing, overcoming the force of the spring, while the cap releases the head. As a result of this, the head opens under the action of aerodynamic forces arising in flight. The air flow entering the container throws off the lid, as a result of which the parachute flies out of the container.

 The use of complex controlled lock devices and other mechanisms and means of forcing the parachute system into operation increases the dimensions and weight of the system design, complicates its maintenance, and also reduces the reliability of the system.

 The technical result of the invention is the creation of a system for entering the aircraft from a corkscrew, independent of the structure of the aircraft, while maintaining the integrity of the structure and aerodynamics of the aircraft during flight tests, in addition, performed without the use of complex controlled lock devices and other mechanisms and means of forcing the input process in operation of the parachute system, and providing completeness, small dimensions and weight of the structure, simplicity and safety of service systems in operation.

 The technical result consists in reducing the parachute release cycle, increasing reliability while maintaining the invariability of the aircraft structure and its aerodynamic characteristics, and the simplicity and safety of service and the independence of the proposed system from the type of aircraft are achieved.

 The task is ensured by the fact that in the system for withdrawing from the corkscrew of the aircraft, containing a container made in the form of a pipe, a parachute device with a main and exhaust parachute, a pyrotechnic mechanism for shooting cargo with a shot load and a racket, according to the invention, a container with a front and removable tail fairings and an open end face mounted on the external suspension via attachment points parallel to the contour of the tail of the fuselage, outside the pipe on the upper tail part at the outlet end placed indoor tail fairing pyrotechnic mechanism shoot load which is connected via a connecting link of the parachute device with a cover extractor parachute raschekovochnoe unit fixed outside the pipe under the same radome.

 In the middle part of the pipe, a longitudinal guide channel of rectangular cross section is made, in which there is a transition device made of two elements connected by a shear pin, one of the elements is connected to the main parachute link, the other through an additional short parachute device link with the power mount, and the adapter is fixed from abnormal movement along the channel with a binding that breaks when the power link of the parachute is pulled during its opening.

 Inside the pipe in its front part on a vertical longitudinal wall are mounted two sequentially mounted on detachable clamps of a pyro-cutter, through which the mentioned additional short link of the parachute device is passed. In the pipe wall there is a top hole and side auxiliary holes closed by easily removable covers, and in the front part of the pipe under the front removable cowl there is a safety device for opening electrical control circuits in the form of a group of contacts and a disconnecting element in the form of a rod.

 Thus, the system is autonomous, easily removable and universal, independent of the design of the aircraft.

 The invention is illustrated by drawings, where in FIG. 1 - given a side view of the proposed system; FIG. 2 is a section along AA of FIG. one; FIG. 3 - shows the placement of the system on the aircraft.

 The aircraft exit system from the corkscrew (Fig. 1-3) contains a removable container 1 mounted on an external sling parallel to the contour of the fuselage tail by means of attachment points 2 located in the lower part of the fuselage along the axis of symmetry of the aircraft.

 The container is made in the form of a cylindrical pipe 3 with a front removable fairing 4, which ensures the aerodynamic quality of the container, and tail removable stoppers 5. Inside the pipe, a cylindrical section 6 with an output open end 7 is made in its tail part.

 In the container there is a parachute device 8 with a main parachute 9 in the chamber and an exhaust parachute 10 in the case.

 The parachute device is equipped with an additional short power link 11, which is cut when the parachute is dropped after its use. The lengths of the connecting links of the parachute device are calculated in such a way that the removal of the hood of the exhaust parachute and its opening, as well as the removal of the camera of the main parachute and its opening, occur after tensioning the corresponding connecting links at a sufficient distance from the aircraft in the zone of steady air flow, which ensures guaranteed filling of the parachutes and their work in the calculated mode without the use of special means of influence on this process.

 In the middle part of the container, a longitudinal guide channel of rectangular cross section 12 is made, in which there is a transition device 13 of two elements connected by a shear pin 14, one of the elements 15 is connected to the link 16 of the main parachute, the other 17 through a short power link 11 of the parachute device with the power mount 18, on a vertical longitudinal wall 19 inside the pipe 3.

 The stud 14 is installed between the link of the main parachute and the link mounted on the wall of the container. When a plane is accelerated to a certain speed, a cut of the stud ensures that the parachute is dropped after it is used if the cut link of the parachute device is not cut for one reason or another. The transition device 13 itself is tied with a thread to the wall of the longitudinal channel 12.

 Outside the container, on the upper tail part at the output end 7, there is a pyrotechnic mechanism 20 closed by a tail fairing 5, the shot load 21 of which is connected through the connecting link 22 of the parachute device to the hood of the exhaust parachute 10.

 Stripping link 23 is fixed outside the pipe under the same cowl 5.

 Inside the container in its front part, on a vertical longitudinal wall 19 are mounted two sequentially mounted on detachable collars 24 of the pyro-cutter 21, through which an additional short link 11 of the parachute device is passed.

 An upper hole is made in the container wall, closed by a lid 26 to lead outside the stripping link and side auxiliary openings with lids 26, which provide free access to the power link 11 of the parachute device, to the link of the main parachute 16, to the installation of pyro-cutters 25 and the transition device 13 during installation system.

 Outside the container, there are mounted the attachment points of the pyrotechnic mechanism 20 for shooting the cargo, the attachment point 27 of the stripping unit of the parachute device, as well as the power units 28 for attaching the container to the aircraft.

 In the front of the container 3, under the removable fairing 4, a safety device for opening the electrical control circuits 29 is located. The disconnecting element is a stud 30 in the form of a rod with a flag attached to it.

 System operation.

 Immediately before the flight, with the possible use of the aircraft’s withdrawal system from the corkscrew, the safety pin 30 is removed from the safety device 29, as a result of which the electrical circuits of the pyrotechnic mechanism 20 and the pyro-cutters 25 are closed, thereby allowing passage to release and discharge of the parachute.

 To withdraw the aircraft from the corkscrew, a command is sent to supply voltage to the pyrotechnic mechanism 20, a shot occurs. The shooted cargo 21 flies out at the required speed, carries with it the connecting link 22 of the parachute device, after the tension of which the packaging of the exhaust parachute 10 is drawn from the open end face 7 of the pipe 3 of the container 1.

 When the package leaves the aircraft at the estimated distance, the central line of the exhaust parachute is pulled, the cover is pulled off the exhaust parachute and flies away with the cargo.

 An exhaust parachute opens in the air stream, strikes and removes the packaging of the main parachute from the container. The power link 16 of the main parachute, fixed inside the container through the adapter 13 and the short power link 11 of the parachute device 8 to the power attachment point, 18, is stretched when the package of the main parachute leaves the estimated distance from the aircraft. The force of the exhaust parachute 10 from the packaging of the main parachute draws the camera. The main parachute 9 opens in the air stream and transmits a braking impulse to the aircraft, as a result of which the aircraft stabilizes its position in space and as a result leaves the tailspin.

 Then, to reset the parachute, voltage is supplied to the pyro-cutters 25, which cut the short power link 11, as a result of which the parachute is reset.

 In case of parachute failure due to the failure of both pyro-cutters, the pilot - increases the flight speed of the aircraft to a value at which the braking force of the towed parachute becomes sufficient to cut the stud 14 of the adapter 13.

 The pin is cut off, releases the power link 16 of the parachute together with the element 15 of the transition device 13, the parachute is reset.

Claims (1)

 A system for withdrawing an aircraft from a corkscrew containing a container made in the form of a pipe mounted parallel to the rear of the fuselage with a parachute device and a mechanism for shooting cargo, characterized in that the container with front and rear removable fairings and an open outlet end is mounted on the external suspension via attachment points, outside the container on its upper tail part at the output end face is a pyrotechnic mechanism closed by a tail fairing, the shot load of which is connected through soy the parachute device has an integral link with an exhaust parachute cover, the stripping link is fixed outside the container under the same fairing, and in the middle part of the container there is a longitudinal guide channel of rectangular cross section, in which there is an adapter made of two elements connected by a shear pin, one of the elements is connected to the link the main parachute, the other through an additional short link of the parachute device with a power mount, while vertically inside the container in front of it longitudinal wall mounted two successively mounted on the detachable collars pirorezaka through which said additional omitted short link parachute force device, in addition to the container wall formed upper opening, and side auxiliary openings closed easily removable lids.

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