DE102006019757A1 - Reconnaissance arrangement for carrier projectile, missiles or aircraft, comprises falling body with sensor unit and with an unit for delaying the fall having rotor blades arranged over articulations at a rotationally mounted rotor head - Google Patents

Abstract

The reconnaissance arrangement for carrier projectile, missiles or aircraft, comprises a falling body with a sensor unit (20) and with unit for delaying the fall aerodynamically arranged at the falling body, which is an oblong body with a head (50). The unit has four rotor blades (30) arranged at a rotationally mounted rotor head over articulations. Each articulation is formed in such a way that in dive operation of the arrangement, the rotor blade is freely pivotable within a pivoting angle area. The reconnaissance arrangement for carrier projectile, missiles or aircraft, comprises a falling body with a sensor unit (20) and with unit for delaying the fall aerodynamically arranged at the falling body, which is an oblong body with a head (50). The unit has four rotor blades (30) arranged at a rotationally mounted rotor head over articulations. Each articulation is formed in such a way that in dive operation of the arrangement, the rotor blade is freely pivotable within a pivoting angle area. The articulation has a stop, which specifies in the V-position of a minimum value for an opening angle. The pivoting angle area passes from a V-position, by which the rotor blade forms an outwardly opened rotation cone with an opening angle opposite to the rotation axis of 60[deg], to a T-position, by which the rotor blade forms the rotation cone with an opening angle opposite to the rotation axis of 80[deg]. The minimum value of the opening angle is 10[deg]. The rotor blades are conveyable into trapped position, when the rotor blades fit at the area of outside surface of the fall body, and have a profile that corresponds to a circular arc. The rotor blades are spirally twisted in the trapped position under prestressing of a spring (80) and are available in the form of concave cylinders. The reconnaissance arrangement is formed as a rupture body.

Description

The Invention relates to a reconnaissance device, the as a throwing body is formed and consisting of a case body with a sensor device and one at the case body arranged, aerodynamic case delay device consists.

A such reconnaissance device is from US H685 (United States Statutory Invention Registration) known. The case delay device has two steering wings on. about an articulation on the case body are the steering wings from a folded position in an unfolded position pivotally. The steering wings are first designed to perform a gliding motion. In the folded Position are the steering wings close to the case body on, leaving the steering wings in the stowage little space. The steering wings point at opposite Corners recesses or bent tabs on. This is intended to be achieved be that the case body additionally makes a rotational movement for gliding flight. In the descent glides the case body helically to the ground. The reconnaissance device indicates additionally still warheads on that while gliding on ground targets can be fired.

• • Beim inneren Abschnitt des Rotorblattes nahe des Zentrums ist die Anströmgeschwindigkeit so klein, dass das Rotorblatt sich im Strömungsabriss befindet.
• • Beim mittleren Abschnitt des Rotorblattes liegen aerodynamische Gesamtkräfte vor, die den Rotor antreiben.
• • Beim äußeren Abschnitt des Rotorblattes liegen die Gesamtkräfte so vor, dass der Rotor abgebremst wird.

On a website (http://www.helikopter-power.de/Der%20Hubschrauber/Autorotation.htm, dated March 24, 2006), the aerodynamics of the autorotation of a rotor blade of a helicopter is described. In autorotation, the rotor blade is divided into an inner, a middle and an outer length section.

• • At the inner portion of the rotor blade near the center, the flow velocity is so small that the rotor blade is stalled.
• • At the middle section of the rotor blade are aerodynamic forces that drive the rotor.
• • At the outer section of the rotor blade, the total forces are such that the rotor is decelerated.

The Interplay between driving and decelerating aerodynamic forces stabilizes the rotational speed of the rotor blade.

Of the Invention is based on the object, a generic reconnaissance device to create, which has good Sinkflugeigenschaften.

• • einer V-Stellung, bei der das Rotorblatt einen nach oben offenen Rotationskegel mit einem Öffnungswinkel gegenüber der Drehachse von 60° bildet, bis zu einer
• • einer T-Stellung, bei der das Rotorblatt einen nach oben offenen Rotationskegel mit einem Öffnungswinkel gegenüber der Drehachse von 80° bildet,

reicht. Nach dem Freigeben der Aufklärungseinrichtung in der Luft stellt sich nach kurzer Zeit die V-Stellung ein. In dieser V-Stellung liegt zum einen die Sinkgeschwindigkeit hoch. Zum andern ist der Abstand zwischen dem Luftangriffspunkt der hochgeklappten Rotorblätter und dem Schwerpunkt hoch. Dies richtet die Aufklärungseinrichtung in senkrechter Richtung aus. Durch die Anströmung der Rotorblätter erhöht sich die Drehzahl. Die Fliehkräfte richten die Rotorblätter in die T-Stellung aus. In der T-Stellung liegt eine niedrige Sinkgeschwindigkeit vor, da der aerodynamische Auftrieb in dieser Stellung am höchsten ist. Denn die Drehzahl und die aerodynamisch wirksame Kreisfläche sind hoch. Auf störende Luftströmungen reagiert die Aufklärungseinrichtung damit, dass kurzzeitig ausgehend von der T-Stellung die V-Stellung eingenommen wird. Die V-Stellung dient der Stabilisierung der Abwärtsbewegung.This object is achieved by the features of claim 1. The case delay device has at least two rotor blades which are designed for autorotation operation. As a result, low descent speeds are achieved. Furthermore, the duration and thus the quality of the Enlightenment increases. Each articulation is designed so that in the descent operation of the reconnaissance device, the rotor blade is freely pivotable within a pivoting angle range and that the pivoting angle range of at least

• A V-position in which the rotor blade forms an upwardly open rotary cone with an opening angle with respect to the axis of rotation of 60 °, up to a
• A T-position in which the rotor blade forms an upwardly open rotary cone with an opening angle with respect to the axis of rotation of 80 °,

enough. After releasing the reconnaissance device in the air, the V position is established after a short time. On the one hand, the rate of descent is high in this V position. On the other hand, the distance between the air attack point of the folded-up rotor blades and the center of gravity is high. This aligns the reconnaissance device in the vertical direction. The flow of the rotor blades increases the speed. The centrifugal forces align the rotor blades in the T position. In the T-position, a low rate of descent is present because the aerodynamic lift is highest in this position. Because the speed and the aerodynamically effective circular area are high. The reconnaissance device responds to disturbing air currents by briefly assuming the V position from the T position. The V position serves to stabilize the downward movement.

According to one Embodiment of the invention, the linkages of the rotor blades have a Stop in the V position, a minimum value for the opening angle pretends. This achieves that the rotor blades so be streamed from below can, that the autorotation operation associated with a transition in the T position preferably can be done quickly.

According to one Another embodiment of the invention, the minimum value of the opening angle is 10 °.

According to one Another embodiment of the invention is the case body elongated body with a head and the rotor blades are hinged on the head. While descent is the fall delay device and thus the air raid point is located at the top. The distance between Air attack point and center of gravity of the case is high. This gives a stable descent.

According to a further embodiment of the invention, the rotor blades are arranged on a rotatably mounted rotor head. This decouples you the rotational movement of the rotor blades, so that the sensor device is ideally rotationally free. This simplifies the evaluation of the sensor data.

According to one Another embodiment of the invention, the linkage is designed so that the rotor blades can be brought into a folded position, in which the rotor blades on Areas of the lateral surface of the case body issue. This reduces the space requirement.

According to one Another embodiment of the invention, the rotor blades Profile on, that at least approximated corresponds to a circular arc. This profile is easy to manufacture. With a corresponding cylindrical design of the case body results a small footprint in the folded position.

According to one Another embodiment of the invention, the rotor blades are in the folded position helically twisted. The advantage This training is that the rotor blades get an in-entanglement. The entanglement angle increases with increasing proximity to Axis of rotation. this leads to to good aerodynamic properties. Is the case body cylindrical formed, the helical rotation takes place in the folded Position around the case body around.

According to one Another embodiment of the invention, at least 4 rotor blades are present, the in the folded position approximated the shape of a hollow cylinder form. In the retracted position, the rotor blades are closed a mechanically very stable, circumferential and shot in profile Form arranged, which thereby high forces in the stowage position withstand. While the individual rotor blades for themselves considered to be slightly bent, dented or twisted they are protected in the stowage. This benefits the functional safety. The profile of the rotor blades is approximated a circular arc. The individual arcs form in the folded Position approximated the shape of a hollow cylinder. Appropriately means that on the one hand always deviates from an ideal form in terms of production technology. Furthermore, can the approximate Form of the hollow cylinder also result in that a versatile Hollow prism is present. After all the shape of a hollow cylinder can therefore be approximated when the wings go through shaping measures, like casting, Forming or machining, in terms of aerodynamics or the lightweight construction a flaring, bead or material recess exhibit. The space inside the hollow cylinder can be occupied by the falling body become. This means that the enclosed space of the hollow cylinder is utilized and you achieve a high packing density. Are sensitive Devices of the case body, such as the sensor device, in the stowage position within of the hollow cylinder, they are mechanically protected until use.

According to one Another embodiment of the invention, the rotor blades are in the folded position under the bias of a spring. This facilitates the unfolding of the rotor blades and prevents them from folding back.

embodiments The invention will be described in more detail below with reference to the drawings. Showing:

1 a reconnaissance device, in an exploded view;

2 to 4 single, enlarged components of the in 1 illustrated reconnaissance device, namely a rotor blade, a rotor head and a hub;

5 in the 1 shown reconnaissance device in longitudinal section, such that the left half shows the reconnaissance device in the retracted position and the right half represents the capped position, wherein the rotor blades are shown simplified;

6 an enlarged detail of the longitudinal section shown 5 such that the area of the rotary bearing of the rotor head is highlighted;

7 to 10 the Aufklärungseinrichtung, each in perspective view, wherein in steps of the process of unfolding the rotor blades is shown;

11 a sectional view of in 7 illustrated Aufklärungseinrichtung in the retracted position, the sectional profile of this sectional view in 7 marked with XI-XI.

The 1 and the associated sectional views 5 and 6 show a reconnaissance device 1 , which is designed as a discharge body and consisting of a case body 10 with a sensor device 20 and an aerodynamic case retarding device arranged on the falling body.

The case delay device has at least two rotor blades 30 on, which are designed for autorotation operation. Every rotor blade 30 is over a linkage 40 at the case body 10 arranged.

• • einer V-Stellung, bei der das Rotorblatt 30 einen nach oben offenen Rotationskegel mit einem Öffnungswinkel gegenüber der Drehachse von 60° bildet, bis zu einer
• • einer T-Stellung, bei der das Rotorblatt 30 einen nach oben offenen Rotationskegel mit einem Öffnungswinkel gegenüber der Drehachse von 80° bildet,

reicht. Die vorgenannten Merkmale werden nachfolgend an Hand der 7 bis 10 beschrieben.Each linkage is designed so that in descending operation of the reconnaissance device the rotor blade 30 is freely pivotable within a pivoting angle range and that the pivoting angle range of at least

• • a V-position, where the rotor blade 30 forms an upwardly open rotary cone with an opening angle with respect to the axis of rotation of 60 °, up to a
• • a T-position, where the rotor blade 30 forms an upwardly open rotary cone with an opening angle with respect to the axis of rotation of 80 °,

enough. The aforementioned features are described below with reference to the 7 to 10 described.

The 7 shows the rotor blades 30 in the retracted position immediately after the reconnaissance device has been released or ejected in the air. The rotor blades 30 are in the folded position under the bias of a spring 80 , as 5 and 6 demonstrate. With the help of the spring 80 fold the rotor blades 30 on.

The reconnaissance device 1 with partially opened rotor blades 30 shows 8th ,

By the flow of air from below is a steady and rapid transition to the V-position, in the 9 is illustrated. In the V position, the air attack point is further above the center of gravity, as the rotor blades 30 are folded up. This means that the reconnaissance device 1 Aligned with respect to its longitudinal axis almost parallel to the attractive force of the earth and stabilized in this vertical orientation.

The articulation of the rotor blades 30 has a stop which predetermines a minimum value for the opening angle φ in the V position. 6 shows that the stop in the form of a stop ring 51 is present. The minimum value of the opening angle φ is 10 °. This is enough for the rotor blades 30 yet to inflict so that the autorotation can build. As the rotational speed increases, the centrifugal forces increase. The centrifugal forces cause the rotor blades 30 move from the V position to the T position. In the T position forms the rotor blade 30 an upwardly open rotary cone with an opening angle φ with respect to the axis of rotation of at least 80 °. An opening angle φ of 90 ° will hardly be set in the T-position, since the outward centrifugal force is superimposed with a smaller, upward vertical force.

When transitioning from the V position to the T position, the air attack point slowly shifts downward in the direction of the center of gravity along the axis of rotation. In the transition to the T-position stabilization is increasingly carried out by the autorotation, which is comparable to the spin stabilization of a projectile. While in the V-position, the sinking speed is still high, in the somewhat later T-position is a significantly lower sinking rate. This results from the high buoyancy forces in the T position, due to the high speed of the rotor blades and the large aerodynamically effective circular area of the rotor blades 30 form.

When the creep device is in the T position ( 10 ) and when disturbances such as gusts or a strong wind occur, the reconnaissance device changes into the V position ( 9 ), stabilizes and returns to the T position ( 10 ) back. The reconnaissance device stabilizes independently. The minimum pivot angle range extends, as already explained above, from an opening angle φ of 60 ° up to an opening angle φ of 80 °. This already gives a good stabilizing effect. The stabilizing effect is enhanced if the minimum pivoting angle range extends from an opening angle φ of 45 ° up to an opening angle φ of 80 °.

Off, for example 1 it turns out that the case body 10 an elongated body with a head, and that the rotor blades 30 are hinged at the head.

6 illustrates particularly well that the rotor blades 30 on a rotatably mounted rotor head 50 are arranged. This is the sensor 20 decoupled from the rotational movement. If the sensor is an image sensor, the image evaluation is simplified.

The linkage 40 is designed so that the rotor blades 30 can be brought into a folded position, in which the rotor blades 30 at areas of the lateral surface of the case body 10 issue. The folded position illustrates, for example, the 7 ,

The rotor blades 30 have a profile that at least approximately corresponds to a circular arc.

As in 7 and associated 11 shown are the rotor blades 30 twisted helically. The helical twist causes the rotor blades 30 in the unfolded position have an intrinsic entanglement. The entanglement angle increases with increasing proximity to the axis of rotation 35 to achieve good aerodynamic properties. In other words, one adapts to the respective peripheral speeds with the steadily changing pitch angle over the length of the rotor blades. The self-entanglement is special 2 which is a detail of a rotor leaf 30 represents.

At least 4 Rotor blades are present, which in the folded position approximated the shape of a hollow cylinder 31 form. To 7 has the reconnaissance facility 1 in the folded position approximated to a cylindrical outer shape. A body with this outer shape is easy to stow away and requires little space. The 11 illustrates the aforementioned hollow cylinder 31 coming from the rotor blades 30 is formed. The hollow cylinder 31 forms a protective coat for the case body 10 with the sensor device 20 , Furthermore, the hollow cylinder arrangement also protects each individual rotor blade 30 , The housing 11 of the case body 10 with the sensor device is due to the protection of the hollow cylinder 31 thin-walled and made of plastic, ie made of a material of low strength.

Adjacent rotor blades define a ridge line in the folded position 32 ( 7 With 11 ). Every dash line 32 between adjacent rotor blades 31 in the folded position runs steeply helical with uniform or non-uniform pitch angle.

The subject of the embodiment has 6 rotor blades 30 on. Every rotor blade 30 has a profile that corresponds to a circular arc of 1/6 of a ring. The number of rotor blades 30 will be according to the size of the case 10 selected. The larger the circumference of the drop body 10 , the larger the number of rotor blades 30 , The parameter of the Reynolds number is taken into account. This relationship is not linear.

The left half of the section after 5 illustrates that in the folded position within the enclosed space of the hollow cylinder 31 the sensor device 20 is arranged. This protects the sensitive sensor device 20 in the staging, until the reconnaissance device is used. At the same time, a high packing density is achieved since, in the folded-in position, the enclosed space of the hollow cylinder 31 for the most part of the case body 10 is taken.

• • Variation der In-Sich-Verschränkung der Rotorblätter. Im Falle einer schraubenförmigen Verdrehung kann der Steigungswinkel verändert werden. Der Steigungswinkel kann über die Länge des Rotorblattes unterschiedlich sein.
• • Variation der Lage der Bohrung 34 (2). Die Bohrung ist auf einer Nase 33 angeordnet. Die Nase 33 ist eine Abwinkelung und kann länger oder kürzer ausgebildet sein.
• • Variation des Mindest-Öffnungswinkels der V-Stellung.

The aerodynamic forces can be changed by the following measures in order to make an application-specific adjustment with regard to the descent behavior.

• Variation of the self-entanglement of the rotor blades. In the case of a helical twist, the pitch angle can be changed. The pitch angle may vary over the length of the rotor blade.
• • Variation of the position of the hole 34 ( 2 ). The hole is on a nose 33 arranged. The nose 33 is a bend and can be made longer or shorter.
• • Variation of the minimum opening angle of the V position.

• • Einsetzen des Lagers 70 (6) in den entsprechenden Sitz des Rotorkopfes 50 und Fixierung mit einem Sicherungsring 72.
• • Einbauen der Rotorflügel 30 in den Rotorkopf 50 und Einsetzen der Feder 80.
• • Hierzu weist der Rotorflügel 30 (2 und 3) eine Nase 33 mit einer Bohrung 34 auf. Die Nase 33 schiebt man in einen Schlitz 52 des Rotorkopfes 50. Den Rotorflügel 30 verbindet man mit dem Rotorkopf 50 über einen Gelenkstift 53. Hierzu wird der Gelenkstift 53 durch gegenüberliegende Bohrungen 54 am Schlitz 52 und durch die dazwischen liegende Bohrung 34 der Nase 33 geführt. 6 illustriert die Rotorblätter 30, die um den Gelenkstift 53 verschwenkbar sind. Über Presspassungen und Spielpassungen stellt man sicher, dass die Rotorblätter 30 sich frei verschwenken und die Gelenkstifte 53 sich nicht verschieben können.
• • Einsetzen der Nabe 60 (5) in das Gehäuse 11 und Festschrauben der Nabe 60.
• • Verbinden der vormontierten Einheit des Rotorkopfes 50 mit der vormontierten Einheit der Nabe 60. Hierzu bringt man den Innensitz des Lagers 70 mit dem Außensitz der Nabe 60 zur Deckung und sichert die Stellung mit einem Sicherungsring 71 (6).
• • Einpressen des Anschlagringes 51.

The reconnaissance device can be mounted quickly and easily. For this purpose, only the following steps are necessary:

• • Inserting the bearing 70 ( 6 ) in the corresponding seat of the rotor head 50 and fixation with a circlip 72 ,
• • Installing the rotor blades 30 in the rotor head 50 and inserting the spring 80 ,
• • For this purpose, the rotor blade 30 ( 2 and 3 ) a nose 33 with a hole 34 on. The nose 33 you push in a slot 52 of the rotor head 50 , The rotor wing 30 you connect with the rotor head 50 over a hinge pin 53 , For this purpose, the hinge pin 53 through opposite holes 54 at the slot 52 and through the hole between them 34 the nose 33 guided. 6 illustrates the rotor blades 30 around the hinge pin 53 are pivotable. About press fits and clearance adjustments, make sure that the rotor blades 30 to pivot freely and the hinge pins 53 can not move.
• • Insert the hub 60 ( 5 ) in the housing 11 and tighten the hub 60 ,
• • Connect the preassembled unit of the rotor head 50 with the preassembled unit of the hub 60 , For this one brings the inner seat of the camp 70 with the outer seat of the hub 60 to cover and secures the position with a circlip 71 ( 6 ).
• • Press in the stop ring 51 ,

The The reconnaissance device shown in the drawings is a test specimen was built. The test sample had a diameter of approx. 30 mm, one length of about 150 mm and a weight of about 150 g. The sink rate in the T position was 3 m / s.

The reconnaissance device 1 can be brought to its application height with a carrier missile, missile or aircraft. The reconnaissance facility can be used militarily, police or civilian. In the case of military use, the reconnaissance device may additionally have a combat ammunition. Civilian use may involve meteorological investigations.

1

education institution

10

case body

11

casing

20

sensor device

30

rotor blade

31

hollow cylinder

32

surge line

33

nose

34

drilling

35

axis of rotation

40

linkage

50

rotor head

51

stop ring

52

slot

53

pintle

54

pivotal hole

60

hub

70

camp

71

circlip for inside seat

72

circlip for outdoor seating

80

feather

φ

opening angle

Claims (10)

Reconnaissance facility ( 1 ), which is designed as a discharge body and from a falling body ( 10 ) with a sensor device ( 20 ) and one on the falling body ( 10 ), the case-delay device is characterized in that: 1 ) at least two rotor blades ( 30 ), which are designed for autorotation operation, • that each rotor blade ( 30 ) via a linkage ( 40 ) on the falling body ( 10 ), that each articulation ( 40 ) is designed so that in the descent operation of the reconnaissance device ( 1 ) the rotor blade ( 30 ) is freely pivotable within a pivot angle range and that the pivoting angle range of at least one of a V-position at which the rotor blade ( 30 ) an upwardly open rotary cone with an opening angle (φ) with respect to the axis of rotation ( 35 ) of 60 °, up to a T-position at which the rotor blade ( 30 ) an upwardly open rotary cone with an opening angle (φ) with respect to the axis of rotation ( 35 ) of 80 ° is sufficient. Reconnaissance facility ( 1 ) according to claim 1, characterized in that the linkages ( 40 ) of the rotor blades ( 30 ) have a stop which specifies a minimum value for the opening angle (φ) in the V position. Reconnaissance facility ( 1 ) according to claim 2, characterized in that the minimum value of the opening angle (φ) is 10 °. Reconnaissance facility ( 1 ) according to one of claims 1 to 3, characterized in that • the falling body ( 10 ) is an elongated body with a head, and • that the rotor blades ( 30 ) are hinged at the head. Reconnaissance facility ( 1 ) according to one of claims 1 to 4, characterized in that the rotor blades ( 30 ) on a rotatably mounted rotor head ( 50 ) are arranged. Reconnaissance facility ( 1 ) according to one of claims 1 to 5, characterized in that the articulation ( 40 ) is formed so that the rotor blades ( 30 ) can be brought into a folded position, in which the rotor blades ( 30 ) at areas of the lateral surface of the falling body ( 10 ) issue. Reconnaissance facility ( 1 ) according to claim 6, characterized in that the rotor blades ( 30 ) have a profile that corresponds at least approximately to a circular arc. Reconnaissance facility ( 1 ) according to one of the claims 7, characterized in that the rotor blades ( 30 ) are helically twisted in the folded position. Reconnaissance facility ( 1 ) according to claim 8, characterized in that at least four rotor blades ( 30 ) are present, which in the folded position approximately the shape of a hollow cylinder ( 31 ) form. Reconnaissance facility ( 1 ) according to one of claims 6 to 9, characterized in that the rotor blades ( 30 ) in the folded position under the bias of a spring ( 80 ) stand.