Delay device.

专利摘要:
10 11 577 ABSTRACT A braking device for increasing the drag coefficient or an associated shell at a desired point while in flight is described. The device comprises: at least two braking vane means which, when released, extend substantially symmetrically into a surrounding airstream while said shell is in flight; retaining means for maintaining said at least two vane means in a retracted first position out of said airstream during an initial portion or said flight; releasing means to allow said at least ..two vanes to extend to a second position into said .airstream at a desired point during said flight; said at least two vane means being extended by centrifugal force due to rotation or said associated shell about its axis; and, said at least two vane means further including co-operating means to ensure substantial symmetrical extension into said airstream. B. v. D. I.E. 1 7 r. I 1999 24 DL-S4a 1011577
公开号:NL1011577A
申请号:NL1011577
申请日:1999-03-17
公开日:2016-07-01
发明作者:James Hickey Dennis
申请人:Bae Systems Plc；
IPC主号:

专利说明:

P49038NL00 Wi
Title: Delay device
The invention relates to a device for exerting an aerodynamic retarding force, in particular, although not exclusively, on a ballistic sleeve during flight.
It is advantageous if the accuracy of ballistic sleeves fired by, for example, artillery components can be improved, so that the chance of hitting the intended target is increased and the chance of so-called concomitant damage is reduced. The accuracy of such sleeves is much greater in the azimuth direction than in the longitudinal direction. Thus, an error zone of generally elliptical shape results, the long axis of the ellipse extending longitudinally.
It is possible to change the range of the artillery sleeve during the flight by increasing the deceleration coefficient.
It is proposed to have an artillery sleeve that can receive a course correction to be carried out during the flight. The sleeve is initially oriented such that it misses the target in the longitudinal direction and an aerodynamic brake comes into operation during the flight which causes the sleeve to come down after a shorter flight for the initially set position and much closer to the target than would otherwise be the case to be. In this way it is thought that an error zone with a significantly smaller surface area can be obtained.
However, there are problems associated with applying the deceleration-increasing brakes because the brake must act as symmetrically as possible around the center line of the projectile in order to minimize the possibility that the projectile rotating about its center line becomes unstable while traversing the trajectory.
The present invention has for its object to provide a device with which a substantially symmetrical deceleration force can be exerted about the axis of rotation of the projectile in order to increase its deceleration coefficient during flight.
According to a first aspect of the invention, there is provided a braking device for increasing the deceleration coefficient of an associated projectile during flight, which device comprises: at least two brake fin members which, when released, extend substantially symmetrically in an ambient air flow during the flight of said projectile; retaining means for keeping said at least two fin members in a retracted first position outside said air flow during a starting part of said flight; releasing means for causing said at least two fin members to fold out to a second position in said air stream at a desired point during flight; and wherein said at least two fin members further comprise cooperating means to ensure substantially symmetrical expansion and placement in said air flow.
The brake fin members can be expandable by centrifugal force due to rotation of the associated projectile about its axis.
The device is preferably placed on the nose of the projectile, which may be an artillery sleeve.
Sleeves sometimes reach supersonic speeds during flight and placing the device on the nose of the sleeve assures that the brake fin members can extend into the surrounding air flow itself.
The device may be incorporated in an igniter device disposed on a forward portion of the sleeve and which igniter device reinforces the sleeve and makes it work when required.
The brake fin members may comprise brake fin members which extend substantially perpendicular to the projectile axis in the surrounding air flow. The brake fin members can be pivotable about an inner end such that the centrifugal force generated by the projectile revolving about its center line results in the brake fin members expanding into the air flow.
Swiveling brake fin members are preferred over fin members which are, for example, adapted to slide out into guide air in the air stream under the centrifugal force action. Such sliding fins have a limited surface area available for projecting into the air flow due to the need to maintain sufficient support of the fins within the device to absorb stresses generated therein by the air flow. Furthermore, unless such sliding systems are manufactured with the utmost precision, they will tend to get stuck due to any misalignment. Thus, such sliding systems can be made accordingly more expensive and less efficient in operation.
Pivoting fin members are advantageous under rotating conditions because the distance between the pivot point and the center of gravity of the fin members offers the mechanical advantage that the pivotal fin members can be expanded with less force than said sliding fins due to the torque generated during expansion. Swing fin members also have the advantage that no guide members are required, and thus the incorrect alignment of fin members and their guide members does not cause a problem.
The retaining means may be a cover member that surrounds the brake fin members during an initial portion of the flight to prevent expansion thereof until desired.
The retaining means can be one or more straps or straps.
The retaining means may be latched or hooked on a support or base member such that expansion of the brake fin members is prevented until desired.
The retaining means may be one or more pins that extend in or through at least one brake fin member and a support or base member.
The release means may be explosive release means such as, for example, a small explosive charge or explosive cord, or may include a gas engine device. The release means can be exploded at the desired time by, for example, a radio signal in order to cause the release means to release the brake fin members to place them in the air flow through outward reaching. The release means may cause the holding means to break. Alternatively, the releasing means may cause the retaining means to move to a position which allows the brake fin members to expand.
The releasing means can achieve their purpose by breaking a retaining cover member and / or repelling it from the sleeve.
Alternatively, the releasing means may result in brittle fingers interconnecting the brake fin members breaking together and allowing it to expand through, for example, slots in a nose cover portion.
The release means must be activated at the correct time in order to achieve the desired course correction. The releasing means can, as stated above, be activated by a remote radio signal. The device according to the present invention itself may comprise a radio receiving device for receiving the radio signal remotely and for effecting activation of the releasing means. Alternatively, any such radio receiving device can be connected to an igniter device or to the sleeve itself, the radio receiver being only operatively connected to the releasing means. The remote radio signal can originate from, for example, a ground control station or a reconnaissance aircraft.
Alternatively, the releasing means may be operated as follows using the Global Positioning System (GPS). At a given point in its trajectory, the on-board computer compares the predicted position of the projectile with its actual position as determined by remotely accessing the GPS. The computer then calculates the appropriate time delay at which the brake fin members must be deployed to provide the correct course correction to bring the projectile on course to its intended purpose. The computer then sets a board clock accordingly, and the clock activates the release means after the appropriate time delay.
The brake fin members also utilize cooperating means to ensure that, in use, they expand substantially symmetrically about the axis of the sleeve. Such means may comprise control regions of the brake fin members, the control regions being arranged such that any asymmetrical expansion of radially adjacent fin members would result in mechanical interference between the control region of one fin member and an adjacent part of the other fin member. Thus, if one fin were jammed or jammed in the closed or partially expanded position, the control region of the adjacent fin would prevent the adjacent fin from expanding further and essentially prevent asymmetric expansion from occurring.
Alternatively, interlocking gear teeth may be applied to curved portions of the brake fin members which ensure that they are symmetrically expanded.
The device can be provided with pairs of brake fin members, each pair being positioned axially next to another.
The device may comprise means for preventing the brake fin members from expanding further than desired in the air stream.
The device may be provided with twin blade pairs of brake fin members, the twin blades being axially adjacent to each other. Both blades can be pivoted about an inner end such that the centrifugal force generated by the associated sleeve that rotates about its center line causes both blades of the brake fin members to extend in the air stream. One of the twin blades can be prevented from projecting as far into the air stream as the second of the twin blades. The second of the twin blades can be prevented from protruding further than desired into the air stream by means of retaining means that can be carried by the first blade. The second of the twin blades may overlie the first blade such that support is provided for the second blade by the first blade when both blades are fully expanded. The second blade can advantageously be provided with an elevated area extending in the air stream and thus provide an increased retardation coefficient for the sleeve during the flight.
According to a second aspect of the invention, there is provided an igniter device in which the braking device according to the first aspect of the invention is incorporated.
According to a third aspect of the present invention there is provided a projectile in which the braking device according to the first aspect or the igniter device according to the second aspect of the present invention is incorporated.
In order to better understand the present invention, examples will now be described, but only by way of illustration, with reference to the accompanying drawings, in which:
Figure 1 shows a general cross-sectional view of a conventional sleeve;
Figure 2 shows a schematic cross-section of a device according to the invention;
Figure 3 shows an explanatory view of means for ensuring symmetrical expansion of brake fin members;
Figure 4 shows a front view along an axial axis of the normally expanded brake fins of Figure 3;
Figure 5 shows a view similar to that of Figure 4, but with a fin not normally plotted; and
Figure 6 which shows a front view along an axial axis of a device with two pairs of brake fin members.
Figure 7a shows the shape of a single-leaf brake fin member that is used in Figure 6 and can be used instead of the fins shown in Figures 1-4.
Figure 7b shows an alternative form of a single-leaf brake fin member together with limiting means for preventing the brake fin member from expanding further than desired in the air stream.
Figure 8a shows a front view along a projectile axis of a device with two pairs of single-leaf brake fins, each of the type shown in Figure 7b.
Figure 8 shows a front view along a projection axis of the device shown in Figure 8a, with the two pairs of single-leaf brake fins fully expanded.
Figure 9a shows the two blades of a two-blade brake fin member that can be used in place of the single-leaf versions shown in Figures 7a, 7b, 8a and 8b.
Figure 9b shows a front view along a projection axis of a device with two pairs of two-blade brake fins as shown in Figure 9a, with the fins fully expanded.
Reference is now made to the drawings where the same parts are designated by common reference numerals.
Figure 1 shows a cross-section through a sleeve generally designated by 10 and incorporating a braking device according to the present invention. The sleeve comprises an envelope 12, an igniter device 14 and a brake device 16 according to the present invention at the nose end of the sleeve. The braking device 16 as shown in the schematic cross-section according to Figure 2 comprises a base element 20 which is used for attaching the device 16 to the igniter 14 which is provided with a central column 15 on which the base plate 20 is mounted. The base plate 20 provides support for pivot pins 46, 48 for the rear pair of brake fin members 22. Support for pivot pins 36, 38 for the front pair of 24 brake fin members is provided by a second support plate 39 attached to the central column 15. A cover member 26 provides a aerodynamic nose for the sleeve 10 and also forms the retaining means that hold the two pairs of brake fin members 22, 24 and prevent them from expanding before desired. The nose part 28 of the cover 26 contains a small explosive charge 30 which is ignited by an electrical impulse via a wire 32 to an igniter 34 in the charge 30. The electrical impulse comes from radio receiving means (not shown) connected to the igniter device 14, wherein the radio receiving means themselves are activated by a remote radio signal. The cover 26 can be made of a plastic material and be provided with various form elements (not shown), such as for instance grooves, which cause the cover to break along preferred lines to obtain a desired manner of breaking and separation of the sleeve during flight.
Pair 22 brake fin members is shown in Figure 3, pair 24 is equal to pair 22 but displaced 90 ° around the sleeve axis 18 relative to pair 22. Each pair of brake fin members 22, 24 comprises two separate brake fin members 40, 42, each member being provided with a respective pivot pin 44, 46 about which it can rotate under the influence of centrifugal force through the flight rotating sleeve and when the retaining cover member 26 is repelled by the explosive charge 30. Each member has a control region 48, 50 on the side opposite the pivot pins 44, 46 for the deceleration or braking region 52, 54 of each member. The effect of the control area is to create a potential overlap area indicated by the shaded areas at 56. However, since the two members 40, 42 are in the same plane and have a significant thickness, it is not possible for them to overlap. As a result, it is only possible that both brake fin members expand simultaneously. For example, if brake fin member 40, as shown in Figure 5, crashes for any reason, the tip 60 of the control area 50 abuts the edge 62 of brake or deceleration area 52 and prevents brake fin member 42 from expanding further, thereby causing a substantially symmetrical retarding force around the sleeve axis 18 is maintained. Similarly, if member 42 crashes, point 64 of control area 48 would collide with edge 66 of brake or deceleration area 54 of member 42 and prevent member 40 from expanding further. When both members 40, 42 expand normally, as shown in Figure 4, the points 60, 64 and edges 52, 66 move alongside each other to effect essentially equal and simultaneous expansion of the brake fin members so as to exert and maintain a symmetrical force. around the center of the sleeve 18.
Figure 6 shows a schematic front view of the device 16. Pair of brake fin members 22, 24 are shown expanded, together with pair 22 also shown in the still-retracted position (22) to show the difference between the expanded and retracted positions of the fin members.
In Figure 3, a location indicated at 70 indicates where the tip 60 finally releases the path of the edge 62 during the expansion movement of the brake fin members. Accordingly, there will be a corresponding location (not shown) where the tip 64 releases the trajectory of the edge 66. Once points 60, 64 are past these locations, neither member 40 nor member 42 can exert any influence on the other with regard to its expansion. However, this is not important because jamming or getting stuck will almost only occur in the initial phase of the brake fin member expansion.
Figure 7a shows a single-leaf brake fin member 40 with a pivot pin 46 about which it can rotate under the influence of centrifugal force through the sleeve rotating during the flight. The member 40 can be positioned around a central column 15 (shown in Figure 6). Support for the pivot pin is provided by the base plate 20 or the support plate 39 (both shown in Figure 2). The member 40 is profiled so as to be able to cooperate with other brake fin members as described in relation to Figure 3.
Figure 7b shows a single-leaf brake fin member 72 similar to member 40 (shown in Figure 7a) with a pivot pin 46 but also having a groove 74 and a lip 76. A pivot pin or pin 78 attached to an axially adjacent plate, such as the base plate 20 or support plate 39 (both shown in Figure 2) limits rotational movement of the brake vane member 72 about the pivot pin 46. As the member 72 moves into the air flow, the groove 74 moves together with it, the member 72 being held as the lip 76 at the end of the groove 74 comes into contact with the pin 78.
Figure 8a shows a pair of 80 single-leaf brake fin members axially adjacent to another pair 90. The single-leaf brake fin members 72 and 82 are pivotally mounted at respective locations 46 and 84, the pivot pins 46 and 84 being attached to a base plate 20 or support plate 39 (such as shown in Figure 2). Expansion of the member 72 too far into the air flow is prevented by contacting the pin 78 with the lip 76 of the groove 74. As described with reference to Figure 3, members 72 and 82 are only capable of symmetrically expanding put.
Figure 8b shows both pairs of 80 and 90 single-leaf brake fin members in fully expanded position. The body 72 is pivoted about the pivot pin 46 and is secured against further pivoting as the lip 76 of the groove 74 reaches the pin 78. The pins 78 and 86, which, as described above, limit the movement of the members 72 and 82, also serve as pivot pins for the pair of brake fin members 90 axially adjacent the pair 80. Body 94 rotates around pivot pin 86 and member 92 rotates around the pivot pins 78. Similarly, the pivot pins 46 and 84, about which the members 72 and 82 rotate, serve as the pins that limit the pivotal movement of the respective members 94 and 92. The pivot pins 46, 78, 84 and 86 are mounted on a base plate 20 and a support plate 39, as shown in Figure 2.
Figure 9a shows two blades 102 and 104 which together form a two-blade brake fin assembly 100. The blade 102 is similar to the member 72 shown in Figure 7b. The blade 102 rotates around a pivot pin 46 mounted on a base plate 20 or support plate 39 (shown in Figure 2). This rotational movement is limited by the lip 76 of the groove 74 upon reaching a pivot pin or pin such as 78 (shown in Figure 7b), which is mounted on a base plate 20 or a support plate 39 (shown in Figure 2). A pin 106 is also attached to the blade 102. The blade 104 is designed so that it fits axially next to the unexpanded blade 102, such that both baths 102 and 104 are capable of rotating the pivot pin 46. The blade 104 is provided with a groove 108 which is axially adjacent the groove 74 if the blades 102 and 104 are not expanded. The groove 108 is not provided with a lip. The blade 104 is provided with a second closed groove 110 which receives the pin 106 attached to the blade 102. The movement of the blade 104 relative to the blade 102 is limited by the pin 106 when it contacts the ends of the groove 110.
Figure 9b shows two axially adjacent pairs of two-blade brake fin assemblies 110 and 112 in fully expanded position. Sheets 102 and 104 rotate around the pivot pin 46 mounted on a base plate or support member 20. Blade 102 is expanded as far as possible and is secured against further rotation by the pivot pin 78 as it contacts the lip 76 (shown in Figure 9a) of the groove 74. The blade 104 has no lip in the groove 108 and is therefore able to rotate further in the air stream than the blade 102. Rotation of the blade 104 beyond desired angle is prevented by the pin 106 attached to the blade 102 within the groove 110. Blade 102 advantageously supports the blade 104, which would otherwise only be supported in the expanded position by the pivot pin 46. This two-blade arrangement shown in Figure 9b provides a larger braking area than that of the single-blade arrangement shown in Figure 8b.

权利要求:
Claims (33)
[1]
A braking device for increasing the deceleration coefficient of an associated projectile during flight, which device comprises: at least two brake fin members which, when released, extend substantially symmetrically in a surrounding air stream during flight of said projectile; retaining means for keeping said at least two fin members in a retracted first position outside said air flow during a starting part of said flight; releasing means for causing said at least two fin members to fold out to a second position in said air stream at a desired point during said flight; and wherein said at least two fin members further comprise cooperating means to ensure substantially symmetrical expansion in said air flow.
[2]
Device as claimed in claim 1, wherein said at least two brake fin members can be expanded by centrifugal force as a result of rotation of the associated projectile about its axis.
[3]
Device according to claim 1 or 2, wherein said device is placed on a forward part of said associated projectile.
[4]
Device as claimed in any of the foregoing claims, wherein the device is incorporated in an igniter device placed on a forward part of an artillery sleeve.
[5]
5. Device as claimed in any of the foregoing claims, wherein the brake fin members comprise brake fin members which extend substantially perpendicular to the projectile axis in the surrounding air flow.
[6]
6. Device as claimed in claim 5, wherein the brake fin members are pivotable about an inner end such that the centrifugal force generated by the associated projectile revolving about its axis can result in the brake fin members expanding into the air flow.
[7]
Device as claimed in any of the foregoing claims, wherein the retaining means are a cover element which surrounds the brake fin members during an initial part of the flight.
[8]
Device as claimed in any of the claims 1-6, wherein the retaining means are a belt or sling.
[9]
Device as claimed in any of the claims 1-6, wherein the retaining means are a latch or hook.
[10]
Device as claimed in any of the claims 1-6, wherein the retaining means are a pin.
[11]
Device as claimed in claim 10, wherein the pin extends in or through at least one brake fin member and a support or base part.
[12]
Device as claimed in any of the foregoing claims, wherein the releasing means are explosive releasing means.
[13]
Device as claimed in any of the claims 1-11, wherein the releasing means are a gas engine device.
[14]
Device as claimed in any of the foregoing claims, wherein said releasing means can be activated by a remote radio signal.
[15]
Device as claimed in any of the foregoing claims, wherein during use said releasing means cause the breaking of said retaining means.
[16]
Device as claimed in any of the foregoing claims, wherein during use said releasing means allow said retaining means to move to a position which makes it possible for the brake fin members to expand.
[17]
The device of claim 1, wherein the retaining means comprise brittle fingers interconnecting the brake fin members.
[18]
18. Device as claimed in any of the foregoing claims, provided with a radio receiving device incorporated therein.
[19]
The device of claim 18, wherein said radio receiving device is operatively connected to the releasing means.
[20]
Device as claimed in any of the foregoing claims, wherein the releasing means can be operated by using the Global Positioning System.
[21]
An apparatus according to claim 20, provided with an on-board computer for comparing the predicted position of the projectile with its actual position as determined by remote access to the Global Positioning System and then calculating the appropriate time delay at which the brake fin members are to be applied plotted in order to provide the correct course correction.
[22]
An apparatus according to any one of the preceding claims, wherein the brake fin members are provided with control regions of the brake fin members, the control regions being arranged such that any asymmetrical expansion of radially adjacent fin members would result in mechanical interference between the control region of one fin member and an adjacent part of the other fin organ.
[23]
The device of claim 1, wherein the means for ensuring symmetrical expansion are interlocking gear teeth.
[24]
Device as claimed in any of the foregoing claims, wherein the device is provided with pairs of brake fin members, each pair being positioned axially next to another.
[25]
The device of claim 5, wherein said braking device comprises means for preventing said brake vane members from expanding further than desired in the air stream.
[26]
The device of claim 5, wherein each brake vane member is provided with a two-blade brake vane and the two blades of each intended brake vane member are axially adjacent to each other.
[27]
An apparatus according to claim 26, wherein said two-blades are each pivotable about an inner end such that during use the centrifugal force generated by the associated projectile revolving about its center line causes both said two-blades to extend in the air flow.
[28]
Device as claimed in claim 27, wherein means are provided for preventing a first of said two leaves protruding as far into the air flow as a second of said two leaves.
[29]
The apparatus of claim 28, wherein said second of said two-blades is secured against protruding further than desired into the air stream by means of retaining means carried by the first of said two-blades.
[30]
An apparatus according to any of claims 26-29, wherein said second of said two-leaves overlies the first of said two-leaves when both blades are fully expanded, so that support for said second blade is provided by said first blade.
[31]
A device according to any one of the preceding claims, wherein the device comprises pairs of brake fin members, each pair being positioned axially adjacent to another.
[32]
An igniter device that incorporates the brake device according to any one of the preceding claims.
[33]
A projectile that incorporates the braking device of any one of the preceding claims.

类似技术:

---

公开号 | 公开日 | 专利标题

---

NL1011577B1|2016-07-21|Delay device.

---

US5671899A|1997-09-30|Airborne vehicle with wing extension and roll control

---

US4664339A|1987-05-12|Missile appendage deployment mechanism

---

US4869442A|1989-09-26|Self-deploying airfoil

---

US6869043B1|2005-03-22|Deployable flare with simplified design

---

US20130214093A1|2013-08-22|Releasable radome cover

---

US4752052A|1988-06-21|Projectile

---

EP2062006A2|2009-05-27|Delayed tail fin deployment mechanism and method

---

EP1660838B1|2008-02-20|Drag-producing devices

---

FR2578640A1|1986-09-12|MISSILE WITH OVERCALIBRE

---

US6314886B1|2001-11-13|Projectile to be fired from a weapon barrel and stabilized by a guide assembly

---

EP2276998B1|2014-12-17|Apparatus for air brake retention and deployment

---

US6745978B1|2004-06-08|Aerodynamic stabilization of a projectile

---

US20040159227A1|2004-08-19|Apparatus and method for restraining and releasing a control surface

---

US4641802A|1987-02-10|Projectile stabilization system

---

US3768755A|1973-10-30|Carrier projectiles

---

US6978968B1|2005-12-27|Deployable flare for aerodynamically stabilizing a projectile

---

US10393485B1|2019-08-27|Mechanical broadhead

---

US3016827A|1962-01-16|Aerodynamic roll control system

---

NL7808340A|1982-09-01|PROJECTILE WITH SHORT JOB.

---

GB2140136A|1984-11-21|Folding fin assembly for missiles

---

US4805532A|1989-02-21|Deploying arrangement for an on-board targeting device of a bomblet

---

EP1548392A1|2005-06-29|Device for the deployment of the vanes of a projectile

---

JP2680705B2|1997-11-19|Vertical tail folding device for space shuttle aircraft

---

US3850387A|1974-11-26|Deflection device for rocket motor propelled projectiles

同族专利:

---

公开号 | 公开日

---

GB9914390D0|2002-03-06|

---

DE19916028A1|2003-07-17|

---

GB2369420A|2002-05-29|

---

GB9813558D0|2002-03-06|

---

US6682014B1|2004-01-27|

---

FR2860578B1|2006-10-27|

---

DE19916028B4|2012-05-31|

---

NO991105A1|2014-12-01|

---

ITRM990312A1|2000-11-18|

---

AU771164B2|2004-03-18|

---

FR2860578A1|2005-04-08|

---

NL1011577B1|2016-07-21|

---

GB2369420B|2002-09-18|

---

AU2373599A|2002-11-14|

引用文献:

---

公开号 | 申请日 | 公开日 | 申请人 | 专利标题

---

---

US2840326A|1949-12-24|1958-06-24|Martin Co|Aerodynamic brake for aircraft|

---

DE1184673B|1962-04-06|1964-12-31|Kunststofftechnische Studienge|Flying body with expansion elements|

---

US3188958A|1963-03-11|1965-06-15|James D Burke|Range control for a ballistic missile|

---

CH480612A|1967-09-06|1969-10-31|Oerlikon Buehrle Ag|Rocket with folding tail and braking device|

---

US3643599A|1968-07-22|1972-02-22|Us Navy|Retractable stabilizer fins and drag brakes for missiles|

---

DE2518645C2|1975-04-26|1986-07-17|Rheinmetall GmbH, 4000 Düsseldorf|Twist brake for a payload that can be ejected from a twist projectile|

---

SE416235B|1976-12-27|1980-12-08|Bofors Ab|BRAKE DEVICE FOR ROTATING BODY|

---

US4186900A|1978-01-23|1980-02-05|Carl M. Loeb Trust|Disintegratable aerodynamic brake|

---

US4295617A|1979-10-02|1981-10-20|The United States Of America As Represented By The Secretary Of The Army|Selectable drag brakes for rocket range control|

---

DE3414911A1|1984-04-19|1985-10-24|Dynamit Nobel Ag, 5210 Troisdorf|Missile, especially a ballistic rocket|

---

DE3422231A1|1984-06-15|1985-12-19|Diehl GmbH & Co, 8500 Nürnberg|DEVICE FOR AERODYNAMICALLY BRAKING THE ROTATIONAL MOVEMENT OF A BODY|

---

DE3519892C2|1985-06-04|1987-04-23|Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De|

---

DE3608109C2|1986-03-12|1992-11-12|Diehl Gmbh & Co, 8500 Nuernberg, De|

---

DE3925236A1|1989-07-29|1991-01-31|Rheinmetall Gmbh|IGNITION FOR A BOMBLET BULLET|

---

GB9614133D0|1996-07-05|1997-03-12|Secr Defence|Means for increasing the drag on a munition|

---

US5762291A|1996-10-28|1998-06-09|The United States Of America As Represented By The Secretary Of The Army|Drag control module for stabilized projectiles|

---

US5816531A|1997-02-04|1998-10-06|The United States Of America As Represented By The Secretary Of The Army|Range correction module for a spin stabilized projectile|

---

US5826821A|1997-08-04|1998-10-27|The United States Of America As Represented By The Secretary Of The Army|Drag control module for range correction of a spin stabil|DE10005414B4|2000-02-08|2006-03-30|Rheinmetall W & M Gmbh|Tail stabilized training projectile|

---

US7963442B2|2006-12-14|2011-06-21|Simmonds Precision Products, Inc.|Spin stabilized projectile trajectory control|

---

US8049149B2|2008-05-16|2011-11-01|Raytheon Company|Methods and apparatus for air brake retention and deployment|

---

KR101043308B1|2009-01-30|2011-06-22|국방과학연구소|Method for reducing ranges of test shell, fuse device for reducing ranges and test shell having the same|

---

US8294072B2|2010-05-27|2012-10-23|Raytheon Company|Projectile that includes as needed pressure-relieving wrap-around tail fins|

---

JP5510979B1|2013-02-15|2014-06-04|防衛省技術研究本部長|Resistance wing structure|

---

JP6278780B2|2014-03-28|2018-02-14|株式会社小松製作所|Slewing flying object|

---

US11072415B2|2018-08-24|2021-07-27|Spirit Aerosystems, Inc.|Nacelle aerodynamic spoiler|

---

DE102018009843A1|2018-12-14|2020-06-18|Diehl Defence Gmbh & Co. Kg|Decelerated direct fire with bullet|

法律状态:
2018-11-07| MM| Lapsed because of non-payment of the annual fee|Effective date: 20180401 |

优先权:

---

申请号 | 申请日 | 专利标题

---

GBGB9813558.5A|GB9813558D0|1998-06-24|1998-06-24|Device for exerting drag|

---