DE2143689C3 - Self-propelled missile launched by a carrier aircraft, the take-off direction of which is opposite to the flight direction of the carrier aircraft - Google Patents

Description

The invention relates to a self-propelled missile launched from a carrier aircraft with the aerodynamic stabilization serving wings, whose take-off direction is opposite to The direction of flight of the carrier aircraft is the center of gravity of the mass caused by the burn-up of the engines and aerodynamic pressure point move relative to each other.

In the classic dogfight between fighter planes, every pilot tries to get behind with his plane to maneuver the opponent in order to get the opponent out of this advantageous attack position, for example attack with cannons or missiles.

To repel such an attack, the attacked aircraft must missile, z. B. projectiles or Can fire missiles almost in the opposite direction of flight.

Regardless of the type of defense weapon, the projectile launched or the launched Missile be aerodynamically stable to reach the target. The projectiles from on-board cannons have one very high initial speed so that stability is guaranteed. For fast-flying and small buildings Combat aircraft are forbidden, especially with regard to the large number of electronic ones to be carried Components for reasons of weight and space, the installation of radar or steering gates controlled, on-board cannons arranged in the stern. In the case of rockets that take up little space, however, is generally the initial speed is much smaller than the airspeed of the aircraft, so that the missiles or missiles that have been shot down, as with a launch from a fixed point of view at the beginning of their trajectory, the surrounding air flows into them from the front.

ίο These are relatively slow takeoff missiles namely after they were shot down - due to the high relative movement between the aircraft and the es surrounding air - flowed in from the rear, so that conventional missiles used for the stated purpose immediately become unstable and are not useful for an aimed shot.

To circumvent these problems, it is known from US Pat. No. 3,077,144, one contrary to the To stabilize the flight direction of his carrier aircraft to be launched missile that the carrier aircraft is connected to a launching rail extending over its entire length, into which the one to be fired Missile hung and then accelerated by means of a rocket propellant so that it is after leaving the end rail such a high relative speed with respect to the carrier aircraft shows that he is from the "bow, so already from the front, is flowed against and therefore behaves aerodynamically stable. To the missile already on the carrier like that to accelerate far are large carrier aircraft provided with take-off openings and powerful rocket propellants necessary. It is evident that such a launch procedure should be used with small, agile combat aircraft cannot be used.

DE-PS 11 88 982 is a recoil-driven Missile with a retrievable, accommodated in a main projectile body, for example a photographic one Monitoring device operated; the missile is first about to be monitored Area shot, whereupon the direction of flight of the main projectile body is changed so that it is in turn driven back to the launch site. In the phase of the missile's flight direction reversal If the aerodynamic pressure point moves over the center of gravity of the missile to the other side, so that during the time the pressure point passes the center of gravity the missile is unstable Um To keep the missile stable even in this phase, are according to this patent on the outside of the

Missile nozzles are provided with which the Missile is given such a high spin that the Stability during the reversal phase Direction of movement is maintained. The invention has for its object to be a

Another way to aerodynamically stabilize one from a carrier aircraft against the flight direction of the carrier aircraft taking off missile; tu create that when taking off without additional on Aids to be attached to the carrier aircraft manage,

co so that also conventional missiles for this Launch procedures can be easily converted and combat aircraft can be retrofitted with these missiles can.

This object is thereby achieved according to the invention

solved that in order to achieve a stable trajectory during the starting process, the training and Arrangement of the take-off engine and the geometric shape of the wing is so dimensioned that the initially before

the center of mass aerodynamic pressure point of the missile after its start from the Front side over the center of mass out to the rear side of the missile and the center of mass migrates from the stern side in the direction of the bow and thereby moves with the center of gravity to a (e.g. via a speedometer determinable) time coincides at which the missile relative is approximately at rest to the medium surrounding it.

Such a design of the missile makes the migration of the center of gravity relative to the aerodynamic pressure point, which in itself also with conventional missiles due to the burn-off of the Thrusters occurs to the fact that the missile kept stable from the start even if it was shot down against the direction of flight of the carrier aircraft will. At the start and shortly after the launch there is therefore the aerodynamic pressure point of the Missile seen from the center of mass on the nose side; because the missile but during this In the first phase of flight the air surrounding it flows from the rear of the vehicle, it behaves aerodynamically stable, as the pressure point in the direction of flow is behind the center of gravity As soon as the reference speed of the missile is about zero in relation to the air surrounding it, fall more aerodynamically Pressure point and center of mass together, so that the missile is indifferent at this moment behaves. The missile, which is accelerated further, accordingly points towards the air flow surrounding it a positive speed, so that it is now flown against from the bow side. Through the When the engine burns down, the aerodynamic pressure point moves - as with conventionally used ones Missiles - here against the tail, whereby the missile is stabilized again.

According to a preferred embodiment of the invention, the missile has a marching and a Starting engine on, which is used to influence the displacement of the aerodynamic pressure point relative to the Center of mass can be placed on the tail of the missile and after it has burned down by the the ignition of the cruise engine occurring gas pressure can be separated from the missile as soon as the over a speedometer determinable time is reached at which the aerodynamic pressure point and the center of gravity of the missile approximately coincide.

It is true that even with a missile according to US-PS 30 77 1.44 by the distance of the Engine's center of mass and the aerodynamic pressure point of the missile relative to one another hike; however, this is not used to stabilize the missile. Since the missile after the If the starting device is already in an aerodynamically stable flight phase, the aerodynamic Pressure point during the entire flight behind the center of gravity of the missile.

From DE-PS 11 72 156 is also a self-propelled steerable missile known in which the migration between the center of mass and the aerodynamic pressure point is influenced. The mass distribution of the missile is like this selected and its engine arranged so that when the engine is burning, the distance between the center of gravity and aerodynamic pressure point increases in the longitudinal direction of the missile. The influencing However, the migration of the center of gravity relative to the aerodynamic pressure point serves to reduce the Lift and propulsion components on the total thrust of the missile over its entire flight path to keep approximately constant, in order to thereby keep the missile over this distance under the same conditions to be able to steer. Also with this missile, from a launch site on the ground or from a is shot down while the aircraft is moving slowly, the aerodynamic pressure point lies behind the

ίο center of mass. A migration of the aerodynamic pressure point beyond the center of gravity, as is done according to the invention, is not provided here.
Even in the aforementioned DE-PS 11 88 982, the relative migration between the center of gravity and the aerodynamic pressure point of the missile is not used to stabilize the missile

The invention is explained in more detail in an exemplary embodiment with reference to the drawing represent

Fig. 1 a fighter aircraft with ein.nan its tail arranged missile, which is formed according to uer invention;

Fig. 2 is a schematic representation of the missile

pers according to the invention with an identification of its serodynamic pressure point and its Center of mass and

3 shows a speed diagram for the speed of the missile relative to the air surrounding it;

Fig. 4 to 8 the missile and the position of the aerodynamic pressure point and the center of mass in successive flight phases.

On a fighter 1 is z. B. under the wings or as shown at the tail a missile 2 on a launching frame, not shown, supported by the four mutually perpendicular stabilizing fins 3, hereinafter referred to as wings The weight of this launch engine 4 is the center of gravity 5 of the missile 2 shifted far towards the tail so that the aerodynamic pressure point D, defined in its position by the inflow speed of the air and the arrangement and dimensions of the wings 3, shifted towards the nose side of the aircraft in front of its center of mass 5 lies.

It can be seen that with this assignment of the aerodynamic pressure point D to the center of mass 5, the missile behaves unstably when the flow is incident from the front, as indicated by the arrow 5 in FIG.

As soon as the missile 2 is released from the aircraft 1 after the starter engine 4 has been ignited, the described assignment of the aerodynamic pressure point D and the center of gravity S stabilizes the missile even at low initial speeds relative to the aircraft 1, since it, as in the F i g. 4 indicated by the arrow 5, due to the high speed of the aircraft i, the air flows against it from the tail side. In this phase of flight, which is indicated in Figure 3, in which the relative speed of the missile Vf * is represented t to the surrounding air (velocity vuii) as a function of time with I, that is the missile 2 in relation to the

Air braked. Due to the progressive burn-off of the launch engine 4, the center of gravity S of the missile 2 moves very quickly against its nose, while at the same time the aerodynamic pressure point remains approximately in the position shown in FIG. 4, or only very slowly against the nose of the missile 2 wanders. To the one shown in FIG. 5 shown in the F i g. 3 is denoted by T , the aerodynamic pressure point D and the center of mass 5 of the missile 2 coincide. This point in time is chosen so that the missile practically rests in relation to the air surrounding it. Here, as shown in FIG. 6, a cruise engine 6 of the missile 2 is ignited, the combustion gases of which trigger holding means (not shown) for the launch engine 4, so that it is separated from the missile 2.

To determine the point in time T , for example, a speedometer can be used which ignites the cruise engine when the missile 2 is determined to be stationary in relation to the air surrounding it. A much simpler solution is obtained, however, from the consideration that the speed of the aircraft 1 maintained during aerial battles is constant within very small limits; this depends, among other things, on the accelerations acting on the aircraft 1 during turns, which are approached with the smallest possible radius. For these reasons, it is expedient to design the starting engine 4 for a constant burn time. After the start-up engine 4 has burned down, the center of mass 5 and the aerodynamic pressure point will then approximately coincide, based on the above considerations. After the ignition of the cruise engine 6, the missile is accelerated and from now on, as also shown by the arrow 5 in FIG. 6, the air flows from the front in the usual way. During the acceleration of the missile 2, the aerodynamic pressure point D shifts with respect to the one now lying in front of it

to center of mass 5 against the tail of the missile 2, so that this is in the now following, in the F i g. 3 flight phase labeled II again behaves in a stable manner. Since the aerodynamic pressure point D and the center of gravity S of the missile 2 move further away from one another with increasing speed, the stability of the missile 2 is also continuously increased (FIG. 7).

Especially in the supersonic range, it Knnn be appropriate in the bow of the missile 2, as in the l · ι g. 8 shown

Extend destabilizer fins 7.

With a missile constructed in accordance with the invention for launching one rapidly forward moving carriers against its flight direction are easily the otherwise occurring Difficulties in flight stabilization of aerodynamically unstable bodies avoided. At the same time this secures Construct a /. To defend the attacked Carrier sufficient flight speed of the missile in the direction of its target with low technical and expense.

For this purpose 2 sheets of drawings

Claims (2)

Claims; 1. Self-propelled missile launched by a carrier aircraft, having a take-off and a cruise engine with aerodynamic stabilization wings, the take-off direction of which is opposite to the flight direction of the carrier aircraft and in which the center of gravity and aerodynamic pressure point migrate relative to one another due to the burn-up of the engines that, in order to achieve a stable flight path during the take-off process, the design and arrangement of the launch engine and the geometric shape of the wings are dimensioned so that the aerodynamic pressure point fm of the missile (2) , which is initially in front of the center of mass (S), after its take-off from the nose side over the center of mass to the tail side of the missile and the center of mass migrates from the tail side in the direction of the bow and coincides with the center of gravity at a point in time (e.g. determinable via a speedometer) at which the missile it is approximately at rest relative to the medium surrounding it 2. Missile according to claim 1, characterized in that the missile has a marching engine and a launch engine (6,4) which, for influencing the displacement of the aerodynamic pressure point (D) relative to the center of gravity (S) on the tail of the missile ( 2) can be attached and, after it has burned down, can be separated from the missile by the gas pressure that occurs when the cruise engine is ignited, as soon as the point in time (T) determined by a speedometer is reached at which the aerodynamic pressure point and the center of gravity of the missile approximately coincide.