DE1248483B - Control device for unmanned aerial vehicles - Google Patents

Description

FEDERAL REPUBLIC OF GERMANY

GERMAN

PATENT OFFICE

EDITORIAL

Int. Cl .:

F42b

B 64 d; B 64g
German class: 62 c - 29/10

Number: 1 248 483

File number: C 17313 XI / 62 c

Filing date: August 7, 1958

Opened on: August 24, 1967

The invention relates to a control device for unmanned missiles that are driven by a gas jet are driven according to the recoil principle.

With all missiles driven according to the recoil principle, a desired Course change come about that the propellant gas jet during the propulsion phase is deflected in a corresponding direction with the help of deflection devices. The operation These deflectors are done by servomotors that have one in many embodiments known command transmission system can be controlled.

The steering devices of a missile are in view of the high temperatures of the Gas jet and the small size of the missile made high demands. These steering devices must have a simple structure in order to perform the functions of the missile when occurring high temperatures do not affect it. In addition, the steering device may only require a small amount of space claim. Above all, it must be ensured that the temperature of the gas jet does not change causes on parts of the steering equipment, which about temperature-dependent, undesirable course changes of the missile. Finally, the steering devices must have a set, hold the course value transmitted by the command system so that a flutter or a automatic adjustment is excluded.

This object is achieved according to the invention by an annular, made of temperature-resistant material existing beam deflector solved in a plane perpendicular to the exit direction of the beam is movably mounted and its respective position by control members arranged in pairs is determined, which lie symmetrically in the plane of movement of the beam deflector and each of which is one Control organ of each couple takes effect at a certain moment, thereby forming part of the inner Edge of the beam deflector cuts into the drive beam of the missile.

The controls consist of two pairs of electromagnets, the moving cores of which are rectangular are arranged to each other and in which one electromagnet of each pair is excited at the same time and the annular beam deflector each in the direction of the other opposing electromagnet to shifts, thereby pushing its core back, so that the beam deflector with reference to the missile can be brought into four effective positions.

Control device for unmanned missiles
Applicant:

Pierre Louis Jean Chanut,

Palalda, Pyrenees-Orientales (France)

Representative:

Dipl.-Ing. W. Scherrmann, patent attorney,
Eßlingen / Neckar, Fabrikstr. 9

Named as inventor:

Pierre Louis Jean Chanut,

Palalda, Pyrenees-Orientales (France)

Claimed priority:

France of 9 August 1957 (745 290)

An embodiment of the control device is shown in the drawing. It shows in schematic depiction

F i g. 1 the missile in longitudinal section,
: Fig. 2 the missile of Fig. 1 in a front view,

F i g. 3 shows a section through the missile along the line III-III of FIG. 1,

F i g. 4 shows a section through the missile along the line IV-IV of FIGS

F i g. 5 the wire spool with sheath in a side sectional view.

The missile (FIG. 1) contains a payload 1 with a front part 2 and a launch drive 3 with four nozzles 4, which are arranged in stabilizing fins 5.

The fins 5 (FIG. 2) are symmetrically distributed around the missile, each fin being slightly inclined with respect to the axis of the missile in order to impart a rotational movement about itself to the missile.

A flight drive 6 is arranged immediately behind the launch drive approximately in the center of gravity of the missile; its exhaust gases flow through the thrust pipe 7 and are expelled through the nozzle 8.

The relays 9 and 10 as well as the dry accumulators 11, the distributor 12, the gyro 13 and the two wire spools 14 and 15 are located in the rear part of the missile.

709 638/57

Claims (7)

An annular beam deflector 16 (FIG. 3) is controlled by four electromagnets 17, 18, 19 and 20. The respective position of the beam deflector is determined by impulses which are delivered to the electromagnets 17, 18, 19 and 20 at relatively short time intervals (for example in 10 to 20 per second). Here, the annular beam deflector 16 is repelled by the electromagnets 17 and 18 only during the time when the electromagnets 19 and 20 are not energized. The jet deflector 16, which consists of a fused alloy with high heat resistance, is movably arranged in the rear part of a nozzle 21 (FIG. 4) and is held by a ring or ring 22. A movable core 23 of the electromagnet 20 can be moved in the two bearings 24 and 25; As long as the electromagnet 20 is not energized, both the core 23 and the disk 26 can move freely. The disc 26 can be supported against the stop 28 under the action of the core of the diametrically opposed electromagnet 18, which is excited at this point in time. If, however, the winding 29 of the electromagnet 20 is energized, the armature 27 attracts the disk 26 and the core repels the beam deflector 16. A wire coil 30 contains turns which are glued to one another without a joint and which consist of a current conductor with a small cross section, for example a steel wire with a diameter of 0.2 mm. The coil 30 is firmly attached to a holder 31, the electrical connection to the relay being made via a wire 32. The coil 30 is surrounded by a sleeve 33, the rear part of which is a club-bottle-shaped body of revolution, the generation of which has a turning point 34 which is located approximately halfway between the coil axis and the coil sleeve. As a result of this design, a wire 35 is intended to be gradually fed in the direction of the opening 36. The opening 36 is located in the coil axis, so that the energy, which originates from the centrifugal acceleration caused by the rapid unwinding of the wire, is gradually reduced in order to avoid heating at any point. The inside of the sheath 33 is lined with a fabric that has a very small coefficient of friction. Patent claims: 1. Control device for unmanned missiles, which are driven by a gas jet according to the recoil principle, characterized by an annular beam deflector (16) made of temperature-resistant material, which is movably mounted in a plane perpendicular to the exit direction of the jet and whose respective position is through Each pair of control members (17 to 20) is determined, which are symmetrical in the plane of movement of the beam deflector and of which one control member of each pair is effective at a certain moment, whereby part of the inner edge of the beam deflector (16) in the drive beam of the Missile cuts 2. Control device according to claim 1, characterized in that the control members (17 to 20) consist of two pairs (17, 19; 18, 20) of electromagnets, the movable cores (26) of which are arranged at right angles to one another and in which one at the same time Electromagnet of each pair is energized and the annular beam deflector (16) is moved in the direction of the other opposing electromagnet, thereby pushing back its core, so that the beam deflector (16) can be brought into four effective positions with respect to the missile. 3. Control device according to claim 1, characterized in that the inner diameter of the annular beam deflector (16) is at least as large as the diameter of the gas jet causing the propulsion of the missile. 4. A control device according to claim 1, characterized in that the control members (17, 20) can be operated by electrical means via two entrollende behind the missile lead wires (35) in a known manner, wherein the serving for the transmission of the control pulses lead wires (35) are wound into coils (30) with seamlessly glued turns, which are surrounded by a cylindrical jacket (33) , the rear part of which tapers in the shape of a club bottle to a mouth (36) , whereby the wire can unwind in the axial direction of the coil. 5. Control device according to claim 1, characterized in that a flight drive (6) is arranged in a manner known per se in the vicinity of the center of gravity of the missile immediately behind a take-off drive (3) , the gases of the flight drive discharged via a thrust tube (7) (6), which are ejected through a propulsion nozzle (21) arranged at the stern, interact with the annular jet deflector (16) . 6. Control device according to claim 5, characterized in that the start drive (3 ) arranged in a known manner immediately behind the payload (1) has ejector nozzles (4) , each of which is in the planes of four stabilizing fins ( 5) are arranged. 7. Control device according to claim 2, characterized in that the control pulses for the electromagnet (17 to 20) serving to control the beam deflector (16 ) are issued and coordinated via a gyro (13). Considered publications:
German Patent Nos. 702131, 827 666;
French Patent Nos. 681 570, 939 050; U.S. Patent No. 2,391,865;
Ferd. Müller: "Guide to remote control", Radar-Verlag, 1955. Legacy Patents Considered:
German Patent No. 1019184. For this purpose 2 sheets of drawings 709 638/57 8. 67 © Bundesdruckerei Berlin