FR2783801A1 - METHOD FOR CONTROLLING A SUPERSONIC MACHINE AND SUPERSONIC MACHINE APPLYING THE SAME - Google Patents

Abstract

The invention relates to a method of modifying the flight behavior of a supersonic machine (305) by intervening on the warhead wave (301) which partially envelops the machine during flight at a higher supersonic speed, 'warhead wave (301) being moved apart and / or brought closer by the wedging and / or lowering of parts (303) of the surface of the machine with the aid of adjusting members. The invention also relates to a supersonic craft (305) having an outer surface (302) and a longitudinal axis, provided with at least one adjustment member to act on its behavior in flight, the adjustment member forming the outer surface ( 303) and being located in the zone (302) of the machine enveloped by a warhead wave (301) during flight through the surrounding air, eccentrically with respect to the longitudinal axis, for the setting implementation of the process mentioned above.

Description

The invention relates to a method for modifying flight behavior

  a supersonic craft flying at a higher supersonic speed or at a hypersonic speed much higher than Mach 1 as well as a supersonic craft

  applying this process.

  The guidance of a flying object close to the ground using movable valves, spoilers and rudders is only possible at a subsonic speed or, if necessary, at a supersonic speed close to the limit of the speed of sound. At a higher supersonic speed or at a hypersonic speed, such guidance is too slow and generates too much

great resistance.

  To remedy this problem, we have tried very recently on a machine of the type mentioned above, to locally remove the warhead wave which, in supersonic or hypersonic speed, is wound around the front point of the machine at a short distance, and thus create an increased eccentric hydraulic resistance, opposite the longitudinal axis of the machine, which causes the desired deviation of the machine in

  because of the difference in transverse force.

  To do this, a pressurized fluid is expelled from the surface through an opening formed therein, or a fuel is ejected which, during its combustion, forms a combustion cushion which swells due to its temperature, causing thus a local spacing of the warhead wave. The disadvantage of such an action on a machine or on such a machine lies in the fact that in most cases, it is necessary to load fuel or a pressurized fluid. Even if only the supply air is used as the pressurized fluid, the hydraulic resistance of the flying machine increases in all cases in a non-negligible way. On the other hand, the time required to ignite the fuel and form a flue gas pressure cushion extends

  the response time of the known guidance is disadvantageous.

  A method is also known which consists in bringing the warhead wave closer to this surface by suctioning the layer of air situated between the warhead wave and the surface of the flying object. The present invention aims to solve the main problem, that is to say not to increase, in general, the hydraulic resistance of a flying machine of the type mentioned above, intended in particular for use in

  hypersonic speed near the ground.

  More particularly, it is a question of finding a method of guiding and a guiding also producing a low resistance of the air, while achieving a clearly superior output, and whose realization or operation does not require the embarkation of a fluid

under pressure or fuel.

  To do this, the invention relates to a method of modifying the flight behavior of a supersonic craft by intervention on the warhead wave partially enveloping the craft during its flight at supersonic speed, characterized in that l warhead wave is spread and / or close to the surface of the flying object by at least partial deformation

and at least local to it.

  The invention also relates to a supersonic machine of the type having an outer surface and a longitudinal axis, equipped with at least one adjustment surface to influence its flight behavior, this adjustment surface having the outline of the exterior surface and being situated in the zone of the machine enveloped by a warhead wave during the flight through the surrounding air, eccentrically with respect to the longitudinal axis, characterized in that the adjustment surface comprises adjustment members, allowing to modify the position of the warhead wave in this zone with respect to the initial position by lowering and / or

  approximation of the body contour adjustment surface.

  In accordance with the method according to the invention, and contrary to the current state of the art, the warhead wave is, at least locally, slightly separated by the bulging of the surface of the tip and / or brought closer to the machine flying by the embossing pressure exerted by the action of the

  decrease in air resistance.

  It is thus possible to spread and / or approximate the position of the warhead wave on several points distributed symmetrically around the longitudinal axis of the flying object. The air resistance is reduced by the bumpiness of the surface, and slightly increased by the

  bulge. Overall, its modification is negligible.

  A particular advantage of this process lies in the fact that it is no longer necessary to expel fuel from the flying object, as is the case in the prior art mentioned above. This fuel takes a certain time before igniting and forming a combustion gas cushion, while the effect of the method according to the invention is instantaneously exerted on the warhead wave so as to eliminate the retardation ci -above. The advantages of the invention compared to the process with suction of the warhead wave also mentioned above, reside in a

markedly increased efficiency.

  The realization can be imagined in several ways; thus, the complete nose of the fuselage of the flying vehicle, and / or the profiled nose of its bearing and / or stabilizing surface could receive a superstructure in segments, the different segments then being able to be propped up and / or lowered in order to spread and / or to bring the warhead wave closer to these segments. This embodiment is advantageous for small flying machines and of particularly simple construction. Thus, the segments designed as movable elements of the surface are actuated in the external surface under the warhead wave by means of an adjustment mechanism, controlled by

  discharge air under high pressure.

  The adjusting members can be positioned at any location where the distance from the warhead wave formed by the speed of the flying object is not too great to prevent the displacement of the adjusting members according to the invention can act sufficiently on the position of the warhead wave. The adjustment surface (s) is therefore preferably in the region of the profiled nose or behind a formation of the external surface causing a warhead wave, for example at the birth of a stabilizer whose nose profile deviates from the warhead wave. These

  stabilizers can be conical or similar.

  Several adjustment members may be provided, preferably arranged symmetrically to the longitudinal axis at identical angular distances, preferably in the nose of the flying object and / or in each of the surfaces of the stabilizers. If necessary, it is also possible to provide only one eccentric adjustment member which is sufficient for guiding the flying machine when it rotates.

around its longitudinal axis.

  Preferably, one or each adjustment member can be moved individually to modify the external contour of the flying machine, so that the segment of the surface which is assigned to it, can, as desired, spread or bring closer

the warhead wave.

  Preferably, this movement can be carried out mechanically using rotary elements or levers, preferably driven by an electromagnetic, pneumatic, pyrotechnic or hydraulic device. It is also possible to use the compressed air under the adjustment surface for the displacement of the adjustment members on the surface, the regulation being carried out using slides or valves which are also preferably driven by systems. electromagnetic, pneumatic, pyrotechnic

or hydraulic.

  Preferably, the regulating member located on the side of the longitudinal axis towards which the flying object is to be deflected is lowered in order to reduce overall the air resistance of the flying object at a hypersonic speed, which also allows an improvement in flight behavior by at least a local decrease in air resistance. In the case where the totality of the air resistance must be reduced to guide the flying machine, the guidance procedure should preferably be initiated by the sole

  lowering of the adjusting members.

  However, it is also possible to provide several adjustment members, arranged symmetrically, the position of which is always lowered in flight in a straight line. To make a deviation, the adjustment surface located on the side of the longitudinal axis opposite the desired deviation

is brought closer or raised.

  Finally, it is also possible to provide a series of adjustment members, arranged symmetrically and which can be brought closer or lowered simultaneously in order to increase or decrease the resistance of the total air to act on the duration of the flight time. of the machine, which results in axial guidance. The asymmetrical approximation or lowering of the adjustment members involves a component of

preferential radial guidance.

  The invention is described in more detail using the following schematic figures attached as

examples:

  Fig. 1 represents a flying object according to the invention, in longitudinal section and in a highly diagrammatic representation, in flight at a hypersonic speed and in a straight line, a) the object with guidance activated by the lowering of the adjustment surface, and b) the machine with guidance activated by setting the

adjustment surface.

  Fig. 2 represents a possibility of segmenting the contour of the surface by circular segments in the shape of a star, FIG. 3 represents a possibility of lowering or wedging the circular segments by way of example, FIG. 4 represents an advantageous segmentation into segments

shaped like a bar.

  The drawing of fig. 1 represents a cone in longitudinal section intended to diagrammatically visualize a part

or the tip of a flying object 305.

  A real flying object, for example an energy projectile

  kinetic, however, is significantly longer than this cone.

  The flying object 305 is produced so as to rotate symmetrically with respect to its longitudinal axis 306 and has an external surface 302 formed by a surface

  receding side and a flat rear surface.

  -7 The drawing in fig. 1 represents the case where the craft is in flight, the surrounding air blowing from left to right in

the direction of the longitudinal axis 306.

  Since the air blows at supersonic, even hypersonic speed, a warp wave 301 is formed at the tip of the conical device, the appearance of which is also conical, presenting a vertical angle which, depending on the blowing speed, is only slightly greater than

  that of the conical flying machine 305.

  Fig. 1 shows the physical principle of the invention. The surface 302 of the flying machine 305 is deformable in a defined manner. The position of the warhead wave 301 is for example modified by the lowering of an element 303 of the outline of the body 302 in this zone relative to its initial position (FIG. 1a). To avoid reduction, the area 303 concerned is enlarged. In this case, the warhead wave 301 is located closer to the body, and the gas pressure exerted on the lowered segment of the surface decreases relatively more strongly than the enlargement of the surface. During the calibration presented in fig. lb, the gas pressure exerted on the wedged part of the body increases. The edge from 302 to 303 does not pose

  mechanical problem of fluids.

  Fig. the visualizes the direction of the dynamic effect 304 during the lowering of a segment of the surface 303 of the contour of the body 302. The setting of a part of the contour 302 to 303 results in an inverted dynamic effect, see fig. lb. The nose of the flying object (rear view cf. fig. 2) can be divided into circular segments 307. Depending on the embodiment, each of these segments can be set or lowered independently of the others with respect to the normal position; the lowering and / or setting of several segments simultaneously is also possible. Fig. 3a shows for example the external contour during the lowering of one of the segments of the body, FIG. 3b during a dynamic effect oriented in

  the same direction by lowering and wedging.

  Besides circular segmentation, the division can also be carried out in bar-shaped segments, as shown in fig. 4 using a cut through the nose of a projectile. Depending on the technical embodiment, the bars 308, inserted flush with the surface, can be raised or lowered independently of each other. Fig. 4b shows a setting and a lowering

similar.

  The position of the warhead wave around additional structures such as planes or stabilizers can be modified by their surface deformations on retractable or telescopic planes or on elements of the planes behind a projectile, any keeping a closed outline. It is possible to provide simultaneous adjustment members on the nose and on other additional structures. The device described is an embodiment among many others, designed to exploit the dynamics transverse to the direction of flight, generated by a variable surface of the nose.

  of a projectile using a guided intervention.

  The essential advantages compared to a known moving point are: a clearly reduced displacement of the masses, a weaker guiding force, a faster reaction of the guiding, smaller and less loaded bearings, simpler bearings, having fewer degrees of freedom a front part of the fixed point (eg for sight or

air inlet).

  Figures 5 to 7 show different sections of an embodiment of such a tip. The movable parts of the surface 21 and 22 as well as 23 and 24 are connected to each other in a mobile manner by hinges 25 and 26. The part 21 is connected in an articulated manner, at the front, to the tip 1 by means of of the bearing 27, the part 24 via the bearing 28. The rear bearings 29 and 30 allow a rotary and longitudinal movement. In the example presented, the hinges 25 and 26 are connected by means of a bar 31 so that the displacement of the parts of the opposite surface is complementary. In addition, the adjustment system must then only supply the difference in the force of the air exerted on the parts 21 and 22 as well as 23 and 24. However, one can also imagine cases where the independent control of the opposite parts of the surface has an advantage; for example if more than two opposite parts of the surface must be moved simultaneously: fig. 6 clearly shows that when the parts 23 and 24 are retracted, the parts 123 and 124 as well as 223 and 224 cannot also be retracted, whereas it is possible to remove the parts 121 and 122 as well as 221 and 222 when the parts 21 and 22

  have come out, and thus enhance the guiding effect.

  In the embodiment described here, the force required to adjust the moving parts of the surface is generated by the dynamic pressure. This embodiment has the following advantage: the force of the air exerted on the outside of the moving parts of the surface is roughly proportional to the dynamic pressure so as to always have the right amount of energy driving, regardless of flight altitude and speed. Discharge air is readily available at the tip. Just accumulate, shoot and embark a

minimum control energy.

  In this example, the discharge air is led through the central channel 11 to the adjustment system 50. A valve 51 is assigned to the unit of the moving parts of the surface 21 and 22; it opens if necessary to allow the discharge air to pass from the chamber 12, through the passage 17, into the chamber 13 as shown in FIG. 7. By the effect of the overpressure, the parts of the surface 21 and 22 are pushed outward, thereby causing the desired deformation of the tip. With the aid of the bar 31, the parts 23 and 24 are driven and withdrawn, thus reinforcing the total effect. The discharge air escapes from the chamber 13 rearwardly through the slot 15 so that the embodiment described does not require an adjusting member for the evacuation (and therefore no sealing system of the room 13). The valves 51, 52, passages 17, 18 and slots 15, 16 are designed and dimensioned so as to be able to maintain the chambers 13 and 14 in

  permanence under sufficiently high pressure.

  In principle, the type of construction of the adjustment members does not affect the operating principle of the control described. In the case where the discharge air must be exploited using only a low energy for the control, the commercially available servo valves are recommended. However, they have the disadvantage of a low opening speed. If the control must respond very quickly, it is possible to use an alternative embodiment with electromagnetic control spherical valves 51 and 52 shown in FIGS. 5 and 7, and a spring pre-tension as a function of the dynamic pressure: the valve springs 53 and 54 are positioned on the movable plate 59. This is connected to the piston 60 on which the pressure of the discharge air conducted in the compartment 56 is exerted through the channel 55. In the compartment 57 opposite it, there is an approximately ambient pressure since it is ventilated via channel 58, then channels 61 and 62. Channels 61 and 62 also serve for the evacuation of air backflow that escapes from other cracks and crevices so that the cost to seal the

  valves 51 and 52 or the piston 60 remains very weak.

  Thanks to this variable pre-tension of the valve springs, the electromagnetic control of the valves can be dimensioned very slightly, although the dynamic pressure exerted on the valves can vary depending on the flight altitude and the speed ( e.g. v = 2000 m / s at h = om: p = 4.5 MPa; v = 1000 m / s at h = 20000 m: p = 0.085 MPa). If the parts of the surface 23 and 24 have to be moved outwards, the movement is triggered by the opening

of valve 52.

  It is also possible to control the position of the parts of the surface 21 to 24 with a single valve, for example, the valve 51. In this case, it should be ensured, using appropriate measures, that in case of ambient pressure in the chamber 13, the parts of the surface 21 and 22 are

  retract and the parts of the surface 23 and 24 come out.

  These measurements can for example be a certain pressure on admission to the chamber 14, or a pre-tension spring, possibly also with an initial tension dependent on the dynamic pressure. The possible downside is

  probably a slow command speed.

  One can also choose an embodiment in which the chambers 13 and 14 are normally under pressure, the variation of the pressure being effected by means of a

controlled ventilation.

  It may be advantageous to equip the entire circumference of a projectile point with movable parts of the surface as shown in FIG. 6. The upper half of fig. 6 shows a section near the bar 31, the lower half has a section at the level of the valve sphere. We can clearly see the special shape of the moving parts of the surface 21 to 24, 121 to 124, 221 to 224. With this embodiment, it is ensured that the parts can move inward and that the chambers 13, 14 , 113, 114, 213, 214 are closed laterally, regardless of the position of the parts of the surface. In this example, the connecting bars 31, 131, 231 are passed through the special wall 2 of the delivery air duct. Of course, other embodiments are possible, including those which pass the bars 31, 131, 231 around the tube 2 or provide for the delivery of discharge air 2 around the

  bars 31, 131, 231, possibly with bifurcations.

  The mechanical system can be simplified considerably by only allowing the movement of parts of the

  surface 21 to 24, 121 to 124, 221 to 224 outwards.

  The mechanical system can be further simplified if the parts of the surface 21 to 24, 121 to 124, 221 to 224 are controlled directly by the actuators. However, this solution requires more powerful actuators which must, in most cases, be oversized (to resist the strongest pressure possibly exerted on the

  surfaces 21 to 24, 121 to 124, 221 to 224).

  The mechanical system can be simplified by the provision of spacers with fixed surface between the moving parts of the surface at 21 to 24, 121 to 124, 221 to 221. The control is then less effective, but the design of the parts of the surface 21 to 24, 121 to 124, 221 to 224 is simpler. The operating principle described can be used with all

the types of actuators possible.

  It is also possible to use the embodiment described for the purpose of controlling, for example, the valves or the pneumatic actuators by means of the differential pressure generated during the flight with a setting angle between the pressure side and the suction side which does not disappear. not. Adequate dimensioning provides a passive control system that opposes and therefore eliminates the inevitable oscillating movements. This mode of suppressing the oscillating movement can be superimposed on a passive control, with the advantage that the adjustment loop of the latter can be produced in a less sophisticated design.

Claims (11)

  1-Method for modifying the flight behavior of a supersonic vehicle by intervention on the warhead wave partially enveloping the vehicle during its flight at supersonic speed, characterized in that the warhead wave is separated and / or close to the surface of the flying object by deformation at   less partial and at least local to it.   2-supersonic machine applying the method according to claim 1 of the type having an outer surface and a longitudinal axis, equipped with at least one adjustment surface to influence its behavior in flight, this adjustment surface having the outline of the exterior surface and being located in the zone of the machine enveloped by a warhead wave during the flight through the surrounding air, eccentrically with respect to the longitudinal axis, characterized in that the adjustment surface is comprised of members adjustment, allowing to modify the position of the warhead wave (301) in this zone with respect to the initial position by lowering and / or bringing the adjustment surface closer (303) of the outline of the body (302).   3-Flying machine according to claim 2, characterized in that the adjustment surfaces (303) are in a star shape (307).   4-Flying machine according to claim 2, characterized in that the adjustment surfaces - (303) are in a bar shape (308).   - Flying machine according to one of claims 2 to 4,   characterized in that the adjusting surfaces (303) are   found in the nose area of the flying object.   6-Flying machine according to one of claims 2 to 5,   having stabilizing surfaces which extend beyond the outer surface, each having a leading edge pointed in the direction of flight, characterized in that the adjusting member (303) or the adjusting members are located in the leading edge area.   7-Flying machine according to one of claims 2 to 6,   characterized in that it comprises adjustment surfaces (303) arranged symmetrically around its axis longitudinal (306).   8-Flying machine according to one of claims 2 to 7,   characterized in that it comprises a control device making it possible to raise and / or lower the adjusting members (303) in order to correct the flight position of the machine steering wheel (305).   9-Flying machine according to one of claims 2 to 8,   characterized in that the angle of incidence or   positioning of the adjusting member (303) is variable.   - Flying machine according to one of claims 2 to 9,   characterized in that the displacement of the respective adjustment surfaces (303) is caused by rotary elements,   sliding elements or levers.   11-Flying machine according to one of claims 2 to 10,   characterized in that the adjustment is controlled by a mechanical, pneumatic, pyrotechnic or hydraulic device.   12-Flying machine according to one of claims 2 to 9,   characterized in that the displacement of the adjusting surfaces (303) is caused by the compressed air under the adjustment surface.   13-Flying machine according to one of claims 2 to 12,   characterized in that the compressed air is regulated by slides or valves driven by mechanical, electromagnetic, pneumatic, pyrotechnic devices or hydraulic.