DE1172156B - Aerodynamically steerable, recoil-propelled flying body - Google Patents

Description

Aerodynamically steerable, recoil-propelled missile. The invention refers to aerodynamically steerable missiles with at least one non-controllable Recoil engine, the burning time of which roughly coincides with the flight time. A such an engine usually delivers a constant thrust.

Missiles of the type mentioned are usually used to transport a Payload from a starting point to a destination whose location also changes during the The approach of the missile can still change. The trajectory of such a missile is in this case by suitable measures, for example by giving steering commands Maintain target course.

Should z. B. reached a relatively distant target by the missile experience has shown that there is enough time even at high airspeeds available to direct the missile into the target.

When the same missile approaches a relatively close target on the other hand, the time is too short for this. The time it takes for a gunner to get the missile under control after takeoff and keep it on target, can only be created here by reducing the flight speed of the missile will.

In known missiles, this is done by increasing the size of the Lift generation and control necessary aerodynamic surfaces achieved. These It is well known that all other things being equal, the smaller the larger the smaller is the airspeed of a missile. By enlarging the aerodynamic However, surfaces are essential for the handiness, transport and storage of such missiles difficult.

It is also known to reduce the airspeed by a large To keep the angle of attack of the flying missile relative to the horizontal small. A large angle of attack usually means deflected control surfaces and thus reduced or even no controllability.

As a result of the difficulties identified are therefore the known Missiles of the type to be considered here for certain distance ranges designed, d. That is, different missiles are to be used for short-range targets than for long-range targets.

It is true that one designed for short-term goals and speaking to Yemen can be slow flying missiles can also be used for long-range targets. But then it's because of its long flight time is highly exposed to the influence of third parties and can among other things can easily be brought out of its orbit. Can also be a moving one Aim slightly out of the steering or impact area of a relatively slowly approaching missile remove. Conversely, however, it is not possible to find one that is suitable for distant destinations and therefore to direct fast-flying missiles safely to short-range targets, as the for Correction of the trajectory required time is not available.

The invention is based on the object of a so-called multi-range missile to realize, which is equally suitable for slow and high-speed flight and accordingly its usability for near and long-distance goals in both areas approximately the same is easy to control.

The solution to this problem is given by an aerodynamically steerable missile with at least one non-adjustable recoil engine, the burning time of which with the Flight time approximately coincides, achieved according to the invention in that also in level flight, the essential means that generate buoyancy is the agent that generates propulsion The engine with its nozzle is whose thrust line of action is the missile's longitudinal axis outside of the migration of the missile pivot point when the propellant burns down affected area, preferably in the direction of the missile tip this area, cuts from below. Here is the inclination of the nozzle opposite the missile longitudinal axis or relative to a horizontal, d. H. considering the angle of attack of the missile, each dimensioned so that the vertical component the thrust together with the lift force of the aerodynamic surfaces of the am Missile attacking gravity corresponds. It is irrelevant from how much Partial thrusts make up the thrust-generating thrust component.

Such missiles therefore need - especially when they are relatively small Airspeeds where it proves to be an essential advantage that the lift-generating The thrust component is independent of the dynamic pressure - only a part of what is otherwise the case with aerodynamic Missiles necessary to generate buoyancy Surfaces and are like Missiles carried solely by aerodynamic forces, also for level flight suitable.

Missiles are known which, in addition to one in the missile longitudinal axis pushing march engine also has a so-called start engine with a Have obliquely to the missile axis pushing nozzle. The line of shear action intersects here the additional engine, which only delivers thrust during part of the flight time and only serves as a starting aid, the missile longitudinal axis, but in each case in the center of gravity of the missile.

This training of missiles thus has the object of the invention nothing in common.

A trained according to the invention missile can during his fly the entire flight time riding on its thrust jet, without major aerodynamic effects Areas for the generation of buoyancy are required, and without at a given aerodynamic area and a given airspeed to generate the required lift the angle of attack of the missile through deflected control surfaces must be enlarged, since the thrust generating engine during the entire flight in addition to propulsion, it also provides a substantial part of the lift.

When using an engine with during the burn time suitable With increasing thrust, such a missile would increase with the flight time have increasing airspeed, i.e. be sufficiently slow in the vicinity, without sacrificing controllability and in the long-range enough quickly to face To be adequately protected against the effects of third parties.

In practice, however, is the implementation of such an engine difficult and associated with additional effort. It also occurs when burning down of the engine, especially in the case of progressively acting propellants, a so-called Wandering the center of gravity of the missile on, which has the consequence that the angle of attack of the missile changes, which in turn changes the proportions of lift and Propulsion components conditional on the total thrust. Here a compensation by swiveling the nozzle or by deflecting the jet is uneconomical.

All of these difficulties become apparent according to a further development of the invention circumvented by the fact that the mass distribution of the missile is chosen and its engine is arranged so that when the engine is burning, the distance between the center of gravity and aerodynamic center point increases in the longitudinal direction of the missile.

In itself, it is true that the balancing of the orbital components in missiles known. However, these known measures are also so-called Starting aids, with the thrust line of action of an additional starting engine only the missile's longitudinal axis intersects, in the center of gravity.

Furthermore, it is with so-called rocket projectiles, so with ballistic Missiles that are provided with stabilizing surfaces and a reaction drive are known, the production-related or due to the combustion process, errors that have an unfavorable effect on flight behavior are therefore as small as possible to keep or to switch off that on the one hand similarly trained and symmetrical nozzles are provided at the same angle obliquely to the projectile axis, whose lines of shear action have a common point of intersection with the longitudinal axis of the storey have and on the other hand the mass distribution of the projectile takes place in such a way that the neutral point behind the center of mass, the effective pivot point between these two points and the intersection of the shear action lines behind the effective one Pivot point, but before the neutral point and before the last quarter of the floor length lies. The focus must be in the first third of the floor.

With such projectiles, a thrust effect is therefore only in the direction the longitudinal axis of the storey provided. A component formation for the longitudinal axis of the storey can only occur as a result of errors and only in the order of magnitude caused by the errors, however, they never make up a substantial part of the lift needed.

In contrast to this, in the subject matter of the invention, there are no focus hikes Suppressive measures are provided, rather it is precisely these that are found in the conventional Missile construction in itself undesirable appearance beneficial use to get over the Compensation of the moments acting on the missile, the angle of attack of such missiles to change depending on the burning time of the propellant charge, in particular a reduction in resistance to achieve the missile.

With such a design of a missile it acts when it is burning Engine a moment that rotates the missile upwards around its transverse axis. The during In contrast, aerodynamic forces acting on the missile during flight cause a moment rotating the missile downwards about its transverse axis. Provided an approximately constant engine thrust is generated when the propellant charge burns off Engine as a result of the shift in the center of gravity to be carried out in the direction of the missile tip the upward turning moment is smaller, so that the counteracting downward turning Moment can take effect. This results in a change in the angle of attack of the Missile relative to the horizontal and thus also a change in the proportions the lift and propulsion components of the total thrust in such a way that the lift-generating Component is smaller and the propulsion generating component is larger. The speed of the missile increases as a result. From the increase in speed of the missile at the same time, the result is that as a result of the increase in the flow velocity of the aerodynamic surfaces an increase in the proportion of the aerodynamically generated Buoyancy adjusts itself to the total buoyancy. This will make the smaller one Proportion of the engine thrust generating component continuously compensated.

In this way it can be done without special means, simply by working together the engine arrangement and the mass distribution according to the invention, achieve, that the speed of such missiles is within predetermined limits, d. H. changes proportionally to the change in position of the center of gravity.

A missile can now initially have a larger angle of attack slowly and with increasing flight time with decreasing angle of attack more quickly fly without using control surfaces to change the angle of attack have to.

This has the further advantage that in addition to relatively small aerodynamic Surfaces also only relatively small control surfaces and accordingly relative small tax payments are required.

A missile designed according to the invention is therefore not only both in its slow flight range and in its fast flight range approximately equally well controllable, but also meets the speed conditions mentioned above with regard to reaching short and long-term goals.

According to a preferred embodiment of the invention, the missile equipped with aerodynamic lift surfaces at the end of the fuselage and has an axially arranged up and propulsion generating thrust components delivering Engine on whose nozzle in a known manner with respect to the missile longitudinal axis intersecting horizontal plane is cranked downwards.

In addition to the advantages already mentioned, there are also benefits from the arrangement of the thrust nozzle at an angle to the longitudinal axis of the missile a favorable one Position of the thrust jet to the assemblies arranged on or in the missile and Components, and in particular for missiles, which are connected via cables by means of electrical Control pulses are remotely controlled, the advantage that the unwinding of this cable from Missile is not affected by the thrust jet.

According to a further feature of the invention, the engine has two Nozzles offset by 180 ° from one another and arranged at an angle to the missile's longitudinal axis different sizes, with the unused nozzle detachably attached by one Cover is closed gas-tight.

By using either of the two nozzles, temperature parameters the propellant charges are compensated, the rate of burning of which is known to be of depends on the outside temperature. A missile designed according to the invention has in other words, almost the same flight characteristics at high and low outside temperatures on. Conversely, when such a missile is used, there are two over the nozzles Choice of speeds.

Everything else about the invention emerges from the description in connection with the drawing, in the more or less schematic example a cross wing aircraft the invention is shown. It shows F i g. 1 an inventive Missile with an obliquely pushing nozzle in section, FIG. 2 the associated force plan, F i g. 3 shows a missile with differently arranged nozzles, FIG. 4 the same Missile in the rear view.

The missile in FIG. 1 with the cross wings 22 and the control members 26 consists of the front part 21, the middle part with engine 23 and the rear part 25. The nozzle 24 of the engine is arranged so that the thrust direction acts obliquely to the missile's longitudinal axis and passes the center of gravity at a distance d. The position of the forces acting on the missile is shown in FIG. 2 shown. At the center of pressure D, the lift A acts, which acts with a lever arm s at the center of gravity S effective at takeoff. The thrust T is broken down into the components Tht and T ,,. Due to the inclination of the thrust direction T against the missile axis by the angle 7, a static equilibrium of forces is achieved. It is A + T " - G = 0. The vertical component of the thrust counteracts the weight of the missile and largely balances it out. The aerodynamic surfaces 22 therefore need to generate no or only very low lift forces A and can accordingly be kept small. The thrust T has a lever arm d in relation to the center of gravity, so that when a certain airspeed is reached after take-off there is equilibrium between the moment of air force of the lift and the moment of thrust. The missile has a certain angle of attack Propellant charge further forward to point S '. The air force moment increases steadily while the thrust moment decreases, so that a top-heavy moment is exerted on the missile that increases with speed horizontally accelerated flight a also with the speed. The distance s of the pressure center point D from the center of gravity S is chosen so that at the given burning speed of the engine, which causes the center of gravity to migrate over the distance s 'from S to S', a change in the longitudinal moment occurs such that the increase in speed and the reduction in the angle of attack are coordinated in such a way that the forces acting upwards over the duration of the flight remain essentially constant, i.e. equal to the weight.

While the distance s of the center of gravity S from the center of pressure D, at which the lift A acts, increases, the distance d from the line of action of the thrust T decreases. which results in an increasing top-heaviness of the missile, has a stronger effect.

Should the missile for different airspeed ranges be interpretable, there is the possibility of taking this into account within certain limits to wear that several nozzles of different diameters installed and then can be used optionally. This arrangement can also be used advantageously, if there is a temperature-related change in thrust of the engine with the help of another Nozzle should be compensated. The associated arrangement is shown in FIG. 3 shown. The missile is provided with cross wings 32 to which the control members 36 are attached are. The missile fuselage consists of the parts payload 31, engine 33 and Rear part 35 together. On the engine 33, a nozzle 34 is pointing downwards as well another nozzle 37 is connected pointing upwards, which is for a different thrust characteristic is designed. By appropriate angular arrangement it is achieved that with each Nozzle for itself the torque compensation over the respective flight duration according to the Example according to FIG. 2 is assured, so that from the burning of the fuel resulting migration the one described, the angle of attack has a diminishing effect. The upper nozzle 37 is closed by a cap 38, so that the missile flies with the lower nozzle 34 alone. Should the upper nozzle 37 are used for propulsion, the missile is turned over and the one on it Way upward facing nozzle 34 with the cap 38 closed. In this situation is a flight with an acceleration corresponding to the nozzle 37 is possible in the same way.

The invention can be used in the same way for a different number of Nozzles, e.g. B. apply to four nozzles arranged between each two surfaces.

Claims (4)

Claims: 1. Aerodynamically steerable missile with at least one non-controllable recoil engine, the burning time of which corresponds approximately to the flight time, characterized in that, even in horizontal flight, the essential means of generating lift is the propulsion-generating engine (23) with its nozzle (24) , the thrust line of action (T) intersects the missile longitudinal axis from below outside the area affected by the migration of the missile pivot point when the propellant charge burns off. 2. Missile according to claim 1, characterized in that the mass distribution of the missile (21, 22, 25) so chosen and its engine (23) is arranged so that when the engine is burning (23) the distance between the center of gravity (S) and the aerodynamic center (D) itself enlarged in the missile longitudinal direction. 3. A missile according to claims 1 and 2, characterized by arranged at the hull end (25) aerodynamic lift generating surfaces (22) and by an in flight body (21, 22, 25) on the same axis arranged up and power-generating thrust components (T ,, and Th ) delivering engine (23), the nozzle (24) of which is bent downwards in a manner known per se with respect to the horizontal plane intersecting the missile longitudinal axis (cf. FIG. 1). 4. Missile according to claim 3, characterized in that the engine (33) has two nozzles (34, 37) of different sizes offset from one another by 180 ° and arranged obliquely to the missile longitudinal axis, the unused nozzle (37) from a releasably attached cover (38) is sealed gas-tight (see Fig. 3). Considered publications: German Patent Specifications Nos. 1078 903, 1024 808; British Patent No. 773,190; USA: Patent No. 2,801571.