DE1950930A1 - Method of stabilizing the trajectory of a recoil-propelled missile - Google Patents

Description

Method for stabilizing the trajectory of a recoil ¹ QeTiGr ₁ missile

The invention relates to a method for stabilization, the flight path a recoil. ^ propelled missile through the rear of the missile attacking tensile forces,

In a known embodiment, the a launching aircraft body are applied in the desired direction of flight stabilizing tensile forces by a mechanical cable guide, on a drum four ropes are wound in "The ropes run via four guide rollers which are mounted at the ends of an anchored on the ground Cross , to four arms attached to the Hepk of the missile to be launched vertically, also arranged crosswise. When starting dea plug body the ropes roll SiOH So from the drum from that they tn all to equal pieces longer we ^, Duroh

109817/0121

BAÖ

the ropes that remain taut is the axis position of the
Plug body and thus also the direction of thrust and acceleration is determined. After reaching a flight distance of about 50 meters, a speed ensuring a stable trajectory is reached and the arms with their ropes are blasted off the missile; see, 1959 yearbook
of the WGL, page 328 "Veronique".

The invention is based on the object of this stabilization method to simplify and at the same time for horizontally and vertically launching recoil-propelled missiles to make usable.

For horizontally launching missiles are, in particular
when they start from so-called launch tubes, which use a gas generator to generate a missile that accelerates
Have gas pressure, relatively large movements of the missile leaving the launch tube in pitch and yaw planes to observe its center of gravity body from the Auffaßbereich his locating device.

The invention is based on the object of remedying this
create by simple means that neither the missile nor its launching system in an unfavorable way.

Based on the known stabilization process for
perpendicular launching missiles, this task is achieved in horizontally launching missiles in that the
Missile stabilizing rope forces are applied with the help of a single tension member, the tensile force of
Zero different missile angles of attack generates moments that rotate the missile back around its center of gravity.

10 * 817/01 art

The tensile forces generated au thus act as rückfmi-cade moments on the plug body when it finds its focus in the iJick- and / or yaw plane due Str-rtatörungen leaving the launch tube Accelerati-K Ingen Hin him turn .also in the desired original flight direction back and thereby reduce the angle of attack oscillations occurring in the pitch or yaw plane. The returning moments are then unsigned if either the missile rouiopt around its longitudinal axis or the traction element is coiled concentrically to the longitudinal axis of the missile or the traction element acts centrally on the tail of the aircraft.

A further advantage of the method according to the invention is to be seen in the fact that it also occurs during the first flight phase undesirable effects of different thrust vectors with the same immersion depth and / or duration of an in Jt; ii engine jet immersing jet spoiler as a result of different large combustion chamber pressures can be compensated with the help of these Z-irkforces. For this are the tensile forces to be measured in such a way that the undesirably large tax rates can be reduced to the desired level by the returning moments generated by the tensile forces. Does it If you see a missile rotating around its longitudinal axis, there are also rotating disturbance torques due to structural inaccuracies reduced in their undesirable effects.

According to a further feature of the invention, the duration and size of the tensile force is dependent on the frequency and the amplitude the undamped angle of attack! vibrations of the missile chosen such that, '; the creation of the desired recirculating conientes at the maximum of an antinode of the angle of attack oscillation is finished to remove this vibration energy from the system.

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10 9 817/0121

Mach a preferred embodiment of the invention To generate the tensile forces, a tensile element coiled concentrically to the longitudinal axis of the missile is provided, which after a advantageous embodiment of the invention that of the steering signal transmission serving cable can be. This is the steering signal transmission Serving cable reinforced at its beginning and with its first turns stronger than the following Coils glued. But it can also be a rope brake for the cable which unwinds from the missile ■ is provided on the missile that depends on the time elapsed since the start can be switched off. Appropriately is then with the cable to connect another traction element, which the forces to be applied transmits between rope brake and missile,

To with the help of a single pulling element both the initially mentioned start spreads as well as the undesired thrust vector changes to compensate for the same immersion duration of the thruster * is according to a further feature of the invention the pulling element in two different ways compared to normal gluing Glued steps.

The invention is described below with reference to a drawing. ,

Show it:

Figure 1 is a schematic representation of its starting device leaving missile,

2 shows a diagram in the pitch plane lying differently influenced by start scattering trajectories, ■ "plotted over time, without acting on the missile tail tensile forces and corresponding trajectories of a missile with a force acting on the rear tractive force ^_v.:. V..

BATH ORIGINAL

"109817/0121

T95093Q

A back to "driven plug body 1 is over one on one here not / turned off coil / in the missile wound Cable 2 is connected to a control center 4 standing on the ground 2, which has a launch tube 5 from which the plug body e.g. is started with the help of a gas generator, also not shown, arranged in the launch tube. That Cable is used to transmit steering signals to the plug body, in the control center as a function of the position of the missile perceived automatically by a locating device 6 can be generated from the target coverage line. About the first thirty meters of this cable are only hinted at Coil 7 glued more firmly than the remaining turns; even if this part of the cable is thicker than the rest of the cable, in order to be able to transmit the necessary tensile forces.

Instead of this more firm bonding, a rope brake can also be provided, which can be switched off via a delay circuit, for example to create the increased initial suction. For this purpose, the cable 2 is to be provided with an additional pulling element, in order to be able to apply the forces without damaging the cable »

The disturbances occurring when leaving the launch tube cause a positive or negative angle of attack 04 of the missile around its center of gravity S as a result of the interference impact M ₁ ', proportional to the angle of attack v / earth, both in the pitch plane shown in FIG. 1 and in the yaw plane (not shown) air forces eraeugt ^ which deviates from the nominal trajectory P trajectories P _{1 0} cause the maximum permissible limits of these different trajectories F are given by the ground clearance and the Äuffaßbereioh A de _f s locating device.

The increased cable pull on the missile, which acts on the center of gravity via the lever arm u , generates a backward rotating moment i / U around the center of gravity, so that the plug path of the missile violates less than the curves Fp In the coaxial to the longitudinal axis of the missile arranged "5"

109817/0121 ■ * " ^0R1GINAL

Figure 2 show. The tensile force to be applied by the traction element is to be selected according to duration and size depending on the frequency and the amplitude of the undamped angle of attack oscillations of the missile, whereby it must be ensured that the generation of the desired return torque is terminated in the maximum of an antinode of the angle of attack oscillation. In the case of missiles with dual engines, ie engines each with an acceleration engine and a cruise engine in a combustion chamber, the use of thrusters becomes undesirably different. Transverse thrust generated with the same immersion depth and immersion time due to the different combustion chamber pressure in the two combustion phases. So far, the necessary compensation has been made by correcting the steering commands, namely by changing the immersion times _? or by means of fluid mechanics, such as changed immersion depths or correction thrusters, ₀ By adapting the reinforced cable pull to the lateral course of the combustion chamber pressure, a constant control effectiveness can be achieved over time «,

To solve both tasks with a single pulling element is the suction element in two opposite the normal gluing un different stages glued

108117/0131

Claims (1)

Claims j 1, process' to stabilize the trajectory of a recoil-V__y-driven missile with the help of rope forces acting on the tail, characterized in that the rope forces are applied with the help of a single traction element (2), the tractive force of which at missile angles of attack («se) other than zero (M ₂ ) generated, which rotate the missile Cl) back around its center of gravity (S) thereby ge ke η η ζ e i c h - that the tensile force depends on duration and size 2ο method according to claim 1, net speed of the frequency and the amplitude of the undamped angle of attack oscillations of the missile (1) are chosen so that the generation of the desired returning torque (Mp) in the maximum of the antinode of the angle of attack oscillation is finished. 3. Device for performing the method according to claims 1 and 2, geke η η ζ eich η et by a tension member (2,7) coiled concentrically to the missile longitudinal axis, 4. Device according to claim 3, characterized in that g e k e η η ζ e 1 c h net that the pulling element (2) that of the steering signal transmission Serving cable (2) is o. "". "" 10 9 817/0121 5 * device according to claims 3 and 4 _r thereby ge - Ic; e_ η η ζ shows that the cable C2J has a reinforced cross-section on its first meters and that its first turns C about 30 meters 1 are stuck together more firmly than the following turns 6 » Device according to claims 3 and 4, geke it: n - ζ calibrate .net by a rope brake arranged on the rear of the missile, which can be switched off via a delay circuit · 7. Device according to claim 4, characterized in that g e k e η η ζ e χ cfe- _net; that the cable {2} has an additional pulling element - .. has »■ ■. ,, "'■, 8 · device according to claim 4 characterized GEK _r & m η ζ ei ch- et η _r that the first meters of the cable have a larger SewicÄt than the subsequent meters · 9 · device according to claims' 3 and 4, characterized _f ge fc e η m ζ η et verifiable that Aaes Zugorgaa in two mutually> on ^ the Kormalverklebung unterschiedlichien stages is glued " 1698-17- / 012 '