CN116101491A - Airborne weapon launching guide rail and airborne cruise weapon backward launching method - Google Patents
Airborne weapon launching guide rail and airborne cruise weapon backward launching method Download PDFInfo
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- CN116101491A CN116101491A CN202310167396.8A CN202310167396A CN116101491A CN 116101491 A CN116101491 A CN 116101491A CN 202310167396 A CN202310167396 A CN 202310167396A CN 116101491 A CN116101491 A CN 116101491A
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- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000010304 firing Methods 0.000 claims description 18
- 238000005096 rolling process Methods 0.000 abstract description 10
- 230000005284 excitation Effects 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 3
- 230000008569 process Effects 0.000 description 5
- 239000000725 suspension Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
- B64D7/08—Arrangements of rocket launchers or releasing means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/0406—Rail launchers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/06—Rocket or torpedo launchers for rockets from aircraft
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F7/00—Launching-apparatus for projecting missiles or projectiles otherwise than from barrels, e.g. using spigots
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Motorcycle And Bicycle Frame (AREA)
- Toys (AREA)
Abstract
The invention discloses an airborne weapon launching guide rail and an airborne cruise weapon backward launching method, wherein the launching guide rail comprises a first guide bracket and a second guide bracket which are oppositely arranged along the width direction of the airborne cruise weapon; the first guide bracket and the second guide bracket are both of inclined I-shaped structures; a first inner side guide groove is formed in one side of the first guide bracket, and a first outer side guide groove is formed in the other side of the first guide bracket; a second inner side guide groove is formed in one side of the second guide bracket, and a second outer side guide groove is formed in the other side of the second guide bracket; each guide groove extends along the length direction of the airborne cruise weapon and is used for sliding fit with a hanging slide block of the airborne cruise weapon. The launching guide rail can effectively inhibit fluctuation of the suspended cruising weapon in the rolling and yaw directions under the vibration excitation effect, and improves launching precision and launching safety.
Description
Technical Field
The invention relates to the technical field of airborne weapon launching, in particular to an airborne weapon launching guide rail and an airborne cruise weapon backward launching method.
Background
The backward ejection emission mode is a novel airborne cruising weapon emission mode. The backward launching process of the airborne cruise weapon comprises the following steps: the cruising weapon is first loaded on the rail; during launching, obtaining an initial speed through an ejection device; after the ejection force is applied, the ejection device continues to slide along the guide rail until the ejection device is separated from the launching device; and then the cruising weapon enters a surrounding flow field to fly in an unsteady flowing pneumatic environment until reaching a starting control point, and the launching process is finished.
In an airborne cruise weapon rearward launch system: the guide rail is large-span and long-distance in appearance form, the cruising weapon is connected with the guide rail through the sliding block, and in the matching form of the guide rail and the sliding block, the common structural form is hung at the two ends of the outer side of the guide rail and the two ends of the inner side of the guide rail by the sliding block. In the whole ejection process, the guide rail has the following functions: supporting the cruise weapon prior to ejection; the movement of the cruising weapon is restrained during the ejection process, and the cruising weapon is guided.
Research shows that random vibration of the moving platform is an important factor affecting the firing safety, and the random vibration brings randomness to the movement of the airborne cruise weapon. To ensure the safety of the backward firing of the airborne cruise weapon, the cruise weapon requires a backward velocity and a downward angular velocity relative to the aircraft. However, when using the conventional launching rail structure, the rail surface and the hanging slider surface generally have a certain amount of clearance in the left-right direction and the up-down direction due to the influence of the aircraft wave. Due to the existence of a chute gap, during launching, the hanging sliding block can collide back and forth up and down and left and right in the guide rail chute, so that the attitude rolling swing, pitching swing and yawing swing of the cruising weapon are caused, the off-orbit launching dynamic parameters of the cruising weapon are scattered in a larger range, and the design value is seriously deviated. The irregular off-orbit attitude threatens the safety of the aircraft and the normal control of cruising weapons. Thus, it is important to study how to attenuate the impact of random vibrations on the firing process of airborne cruise weapons.
The disturbance caused by the vibration of the carrier is unavoidable, so that the invention aims to restrain the disturbance by optimizing the guide rail structure and improving the anti-vibration capability of the system on the premise of not additionally increasing the structural quality, thereby reducing the influence of the vibration excitation of the carrier on the cruise weapon in the slip-off constraint period.
Disclosure of Invention
In view of the above, the invention provides the airborne weapon launching guide rail and the airborne cruise weapon backward launching method, and the launching guide rail can effectively inhibit the fluctuation of the suspended cruise weapon in the rolling and yaw directions under the action of vibration excitation, thereby improving the launching precision and launching safety.
The invention adopts the following specific technical scheme:
the invention provides an airborne weapon launching guide rail, which comprises a first guide bracket and a second guide bracket which are oppositely arranged along the width direction of an airborne cruising weapon; the first guide bracket and the second guide bracket are both of inclined I-shaped structures;
a first inner side guide groove is formed in one side, facing the second guide bracket, of the first guide bracket, and a first outer side guide groove is formed in the other side, facing away from the second guide bracket, of the first guide bracket;
a second inner side guide groove is formed in one side, facing the first guide bracket, of the second guide bracket, and a second outer side guide groove is formed in the other side, facing away from the first guide bracket, of the second guide bracket;
the first inner side guide groove, the first outer side guide groove, the second inner side guide groove and the second outer side guide groove all extend along the length direction of the airborne cruise weapon and are used for being in sliding fit with a hanging sliding block of the airborne cruise weapon.
Further, the first guide bracket and the second guide bracket each comprise a vertical plate arranged along the vertical direction, two parallel outer guide plates fixedly connected to the inner side surface of the vertical plate, and two parallel inner guide plates fixedly connected to the outer side surface of the vertical plate; the outer guide plate and the inner guide plate are obliquely arranged and form the same included angle with the vertical plate; the front ends of the outer guide plate and the inner guide plate are aligned;
the first inner side guide groove is formed by surrounding the vertical plate of the first guide bracket and the two inner side guide plates, and the first outer side guide groove is formed by surrounding the vertical plate of the first guide bracket and the two outer side guide plates;
the second inner side guide groove is formed by surrounding the vertical plate of the second guide bracket and the two inner side guide plates, and the second outer side guide groove is formed by surrounding the vertical plate of the second guide bracket and the two outer side guide plates.
Further, the first guide bracket and the second guide bracket are of symmetrical structures;
the outer guide plate and the inner guide plate incline from bottom to top along the direction that the outer guide plate of the first guide bracket faces the inner guide plate;
the included angle is 45-90 degrees.
Further, the first length of the inner guide plate is smaller than the second length of the outer guide plate, and the length difference is the distance between the front hanging sliding block and the rear hanging sliding block of the airborne cruise weapon, so that the front hanging sliding block and the rear hanging sliding block can slide away simultaneously.
Still further, still include fixed connection in first direction support and the connecting plate at second direction support top.
Still further, the hanging slider, the first inner guiding groove, the first outer guiding groove, the second inner guiding groove and the second outer guiding groove are provided with a normal contact gap and a lateral contact gap, and the normal contact gap is smaller than the lateral contact gap.
Further, guide structures are provided at rear end portions of the inner guide plates of the top.
Further, the guiding structure is a circular arc section.
In addition, the invention also provides a backward launching method of the airborne cruise weapon, which adopts the launching guide rail to launch, and the specific launching method comprises the following steps:
the catapulting force acts to drive the airborne cruising weapon to move along the launching guide rail;
the front and rear hanging sliding blocks of the airborne cruising weapon are simultaneously separated from the transmitting guide rail, and the airborne cruising weapon obtains low-head moment through the guiding structure, so that the airborne cruising weapon has positive pitch angle speed;
the airborne cruising weapon retreats and lowers the head relative to the aircraft, so that the aiming line of the airborne cruising weapon points to the ground;
the engine of the airborne cruise weapon ignites, flies to the attack target under the guidance of the braking system, and performs striking.
The beneficial effects are that:
the first guide bracket and the second guide bracket of the airborne weapon launching guide rail are both of inclined I-shaped structures, and the inner side and the outer side of the first guide bracket and the second guide bracket are respectively provided with guide grooves which are in sliding fit with the hanging sliding blocks of the airborne cruise weapon, so that the normal contact force between the hanging sliding blocks and the guide brackets is reduced relative to the moment arm of the centroid of the cruise weapon, and under the disturbance condition, the aircraft weapon launching guide rail has a rolling disturbance power arm smaller than that of the traditional structure, and the aim of reducing the rolling disturbance is fulfilled; meanwhile, the guide rail groove structure enables the lateral contact surface to be free of collision, namely no collision occurs in the gap, so that yaw disturbance is reduced; therefore, the launching guide rail with the structure can restrain rolling fluctuation and yaw fluctuation of the cruising weapon under the random vibration excitation effect, and has the advantages of simple structure, easy realization and no additional increase of the weight of the launching system.
Drawings
FIG. 1 is a schematic diagram of an exploded configuration of an airborne cruise weapon firing system employing an airborne weapon firing guideway of the present invention;
FIG. 2 is a schematic perspective view of the firing rail of the present invention;
FIG. 3 is a cross-sectional view of the firing rail of the airborne weapon of the present invention;
FIG. 4 is a schematic view of the assembled structure of the airborne weapon firing rail and cruise weapon of the present invention;
FIG. 5 is a schematic view of a part of the enlarged structure of the portion A in FIG. 4;
FIG. 6 is a vibration environment of a type of aircraft;
FIG. 7 is a roll angle velocity time-varying curve obtained from an emission simulation experiment based on the vibration environment of a certain type of aircraft;
FIG. 8 is a time-varying plot of yaw rate obtained from an emission simulation experiment based on a vibratory environment of a type of aircraft;
fig. 9 is a schematic diagram of the trajectory of the safe firing and operation of an airborne cruise weapon.
Wherein the aircraft comprises a 1-launching guide rail, a 2-front hanging slide block, a 3-rear hanging slide block, a 4-cruising weapon, a 5-launching frame, a 6-cabin deck connecting component, a 7-aircraft, an 8-trajectory, a 9-target, an 11-first guiding bracket, a 12-second guiding bracket, a 13-first inner guiding groove, a 14-first outer guiding groove, a 15-second inner guiding groove, a 16-second outer guiding groove, a 17-riser, a 18-outer guiding plate, a 19-inner guiding plate, a 20-connecting plate and a 21-arc section
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
Example 1
The embodiment of the invention provides an airborne weapon launching guide rail 1, as shown in fig. 1, a launching frame 5 is fixedly arranged on an airplane 7 through a cabin deck connecting part 6, a hanging space of an airborne cruise weapon 4 is formed inside the launching frame 5, the launching guide rail 1 is fixedly arranged in the launching frame 5 through the top, a front hanging slide block 2 and a rear hanging slide block 3 are fixedly arranged on the top of the airborne cruise weapon 4, and the launching guide rail 1 is hung through the front hanging slide block 2 and the rear hanging slide block 3;
as shown in fig. 2 and 3, the launching guide 1 includes a first guide bracket 11 and a second guide bracket 12 that are disposed opposite to each other in the width direction of the airborne cruise weapon 4; the first guide bracket 11 and the second guide bracket 12 are both of inclined I-shaped structures; the first guide bracket 11 and the second guide bracket 12 may have the same structure or may have different structures, and in this embodiment, the first guide bracket 11 and the second guide bracket 12 having symmetrical structures are described as an example; the distance between the first guide bracket 11 and the second guide bracket 12 can be adjusted according to cruising weapons with different diameters, so that the launching guide rail 1 can adapt to airborne cruising weapons 4 with different sizes;
a first inner guide groove 13 is arranged on one side of the first guide bracket 11 facing the second guide bracket 12, and a first outer guide groove 14 is arranged on the other side of the first guide bracket 11 facing away from the second guide bracket 12;
a second inner guide groove 15 is arranged on one side of the second guide bracket 12 facing the first guide bracket 11, and a second outer guide groove 16 is arranged on the other side of the second guide bracket 12 facing away from the first guide bracket 11;
the first inner guide groove 13, the first outer guide groove 14, the second inner guide groove 15 and the second outer guide groove 16 each extend in the length direction of the airborne cruise weapon 4 and are adapted to slidingly engage with the hanging slide of the airborne cruise weapon 4. As shown in fig. 4, the first inner guide groove 13 and the second inner guide groove 15 cooperate with the front suspension slide 2 of the airborne cruise weapon 4, the first outer guide groove 14 cooperates with one rear suspension slide 3 of the airborne cruise weapon 4, and the second outer guide groove 16 cooperates with the other rear suspension slide 3 of the airborne cruise weapon 4, so as to suspend the airborne cruise weapon 4 within the cradle 5 of the aircraft 7.
In a specific embodiment, as shown in fig. 2 and 3, each of the first guide bracket 11 and the second guide bracket 12 includes a vertical plate 17 disposed in a vertical direction, two parallel outer guide plates 18 fixedly connected to an inner side surface of the vertical plate 17, two parallel inner guide plates 19 fixedly connected to an outer side surface of the vertical plate 17, and a connection plate 20 fixedly connected to top portions of the first guide bracket 11 and the second guide bracket 12; the tops of the first guide bracket 11 and the second guide bracket 12 can be fixedly connected into a whole through the connecting plate 20;
the outer guide plate 18 and the inner guide plate 19 are both obliquely arranged and form the same included angle theta with the vertical plate 17; the included angle theta is 45-90 degrees, such as: 45 °, 60 °, 65 °, 75 °, 80 °, 85 °; the outer guide plate 18 and the inner guide plate 19 are inclined from bottom to top along the direction of the outer guide plate 18 of the first guide bracket 11 towards the inner guide plate 19;
the front ends of the outer guide plate 18 and the inner guide plate 19 are aligned; the outer guide plate 18 and the inner guide plate 19 may have the same length or may have different lengths; when the first length of the inner guide plate 19 is smaller than the second length of the outer guide plate 18, a length difference exists between the rear end part of the outer guide plate 18 and the rear end part of the inner guide plate 19, and the length difference is the distance between the front hanging sliding block 3 and the rear hanging sliding block 3 of the airborne cruise weapon 4, so that the front hanging sliding block 3 and the rear hanging sliding block 3 can slide away simultaneously;
the first inner guide groove 13 is surrounded by the vertical plate 17 of the first guide bracket 11 and the two inner guide plates 19, and the first outer guide groove 14 is surrounded by the vertical plate 17 of the first guide bracket 11 and the two outer guide plates 18;
the second inner guide groove 15 is surrounded by the riser 17 of the second guide bracket 12 and the two inner guide plates 19, and the second outer guide groove 16 is surrounded by the riser 17 of the second guide bracket 12 and the two outer guide plates 18.
Further, the hanging slider has a normal contact gap and a lateral contact gap with the first inner side guide groove 13, the first outer side guide groove 14, the second inner side guide groove 15, and the second outer side guide groove 16, and the normal contact gap is smaller than the lateral contact gap.
Specifically, guide structures are provided at the rear end portions of the inner guide plates 19 at the top; the guiding structure is a circular arc section 21. The guiding structure such as the circular arc section 21 is beneficial to the low head moment generated by the cruising weapon 4 when being launched.
The first guide bracket 11 and the second guide bracket 12 of the airborne weapon launching guide rail 1 are of inclined I-shaped structures, and guide grooves which are in sliding fit with the hanging sliding blocks of the airborne cruise weapon 4 are respectively formed on the inner side and the outer side of the first guide bracket 11 and the second guide bracket 12, so that the normal contact force between the hanging sliding blocks and the guide brackets is reduced relative to the moment arm of the mass center of the cruise weapon 4, and under the disturbance condition, the moment arm is provided with a rolling disturbance power arm smaller than that of the traditional structure, and the aim of reducing rolling disturbance is fulfilled; meanwhile, the guide rail groove structure enables the lateral contact surface to be free of collision, namely no collision occurs in the gap, so that yaw disturbance is reduced; therefore, the launching guide 1 adopting the structure can restrain rolling fluctuation and yaw fluctuation of the cruising weapon 4 under the random vibration excitation, and has simple structure, easy realization and no additional increase of the weight of the launching system.
In the vibration environment as shown in fig. 6, the fluctuation of the roll angle speed and yaw rate of the airborne cruise weapon under the condition of the firing guide rail according to the present invention is shown in fig. 7 and 8, compared with the conventional firing guide rail. According to the result, the launching guide rail can effectively inhibit rolling and yaw fluctuation of the airborne cruise weapon under the random vibration excitation effect.
Example two
The embodiment of the invention also provides a backward launching method of the airborne cruise weapon, which adopts the launching guide rail 1 to launch, as shown in fig. 9, and the specific launching method comprises the following steps:
the ejection force acts to drive the airborne cruise weapon 4 to move along the launching guide rail 1;
the front and rear hanging sliding blocks 3 of the airborne cruise weapon 4 are simultaneously separated from the launching guide rail 1, and the airborne cruise weapon 4 obtains low head moment through a guide structure, so that the airborne cruise weapon 4 has positive pitch angle speed;
the airborne cruise weapon 4 is retracted and lowered relative to the aircraft 7, so that the aiming line of the airborne cruise weapon 4 is directed to the ground;
the engine of the onboard cruise weapon 4 fires, flies towards the attack target 9 according to trajectory 8 under the guidance of the braking system, effecting a hit.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. An airborne weapon launching guide rail, characterized in that the launching guide rail comprises a first guide bracket and a second guide bracket which are oppositely arranged along the width direction of an airborne cruising weapon; the first guide bracket and the second guide bracket are both of inclined I-shaped structures;
a first inner side guide groove is formed in one side, facing the second guide bracket, of the first guide bracket, and a first outer side guide groove is formed in the other side, facing away from the second guide bracket, of the first guide bracket;
a second inner side guide groove is formed in one side, facing the first guide bracket, of the second guide bracket, and a second outer side guide groove is formed in the other side, facing away from the first guide bracket, of the second guide bracket;
the first inner side guide groove, the first outer side guide groove, the second inner side guide groove and the second outer side guide groove all extend along the length direction of the airborne cruise weapon and are used for being in sliding fit with a hanging sliding block of the airborne cruise weapon.
2. The airborne weapon firing guideway of claim 1, wherein the first guide bracket and the second guide bracket each comprise a riser disposed in a vertical direction, two parallel-disposed outboard guide plates fixedly attached to an inboard surface of the riser, and two parallel-disposed inboard guide plates fixedly attached to an outboard surface of the riser; the outer guide plate and the inner guide plate are obliquely arranged and form the same included angle with the vertical plate; the front ends of the outer guide plate and the inner guide plate are aligned;
the first inner side guide groove is formed by surrounding the vertical plate of the first guide bracket and the two inner side guide plates, and the first outer side guide groove is formed by surrounding the vertical plate of the first guide bracket and the two outer side guide plates;
the second inner side guide groove is formed by surrounding the vertical plate of the second guide bracket and the two inner side guide plates, and the second outer side guide groove is formed by surrounding the vertical plate of the second guide bracket and the two outer side guide plates.
3. The airborne weapon firing guideway of claim 2, wherein the first guide bracket and the second guide bracket are symmetrical structures;
the outer guide plate and the inner guide plate incline from bottom to top along the direction that the outer guide plate of the first guide bracket faces the inner guide plate;
the included angle is 45-90 degrees.
4. The airborne weapon firing guideway of claim 3, wherein the first length of the inboard guide plate is less than the second length of the outboard guide plate and the difference in length is the distance between the front and rear hitch sliders of an airborne cruise weapon for effecting simultaneous sliding off of the front and rear hitch sliders.
5. The airborne weapon firing guideway of claim 4, further comprising a connection plate fixedly connected to the tops of the first guide bracket and the second guide bracket.
6. The airborne weapon firing guideway of any one of claims 1-5, wherein the hanging slide has a normal contact gap and a lateral contact gap with the first inboard guide groove, the first outboard guide groove, the second inboard guide groove, and the second outboard guide groove, and the normal contact gap is less than the lateral contact gap.
7. The airborne weapon firing guideway of claim 6, wherein the rear ends of the inboard guide plates at the roof are each provided with a guide structure.
8. The airborne weapon firing guideway of claim 7, wherein the guiding structure is a circular arc segment.
9. A method for backward launching of an airborne cruise weapon, characterized in that the launching is performed by using a launching track according to any one of the claims 8, the specific launching method comprising the steps of:
the catapulting force acts to drive the airborne cruising weapon to move along the launching guide rail;
the front and rear hanging sliding blocks of the airborne cruising weapon are simultaneously separated from the transmitting guide rail, and the airborne cruising weapon obtains low-head moment through the guiding structure, so that the airborne cruising weapon has positive pitch angle speed;
the airborne cruising weapon retreats and lowers the head relative to the aircraft, so that the aiming line of the airborne cruising weapon points to the ground;
the engine of the airborne cruise weapon ignites, flies to the attack target under the guidance of the braking system, and performs striking.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310167396.8A CN116101491B (en) | 2023-02-27 | 2023-02-27 | Airborne weapon launching guide rail and airborne cruise weapon backward launching method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310167396.8A CN116101491B (en) | 2023-02-27 | 2023-02-27 | Airborne weapon launching guide rail and airborne cruise weapon backward launching method |
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| Publication Number | Publication Date |
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| CN116101491A true CN116101491A (en) | 2023-05-12 |
| CN116101491B CN116101491B (en) | 2023-12-01 |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0284756A2 (en) * | 1987-04-01 | 1988-10-05 | Messerschmitt-Bölkow-Blohm Gesellschaft mit beschränkter Haftung | Aircraft mounting for a weapon |
| HK1007348A1 (en) * | 1991-08-08 | 1999-04-09 | Ml Aviat Ltd | Improved rail launcher for airborne missiles |
| EP2098814A1 (en) * | 2008-03-06 | 2009-09-09 | Saab Ab | A missile lauching system, and a hanger member for suspending the missile in a lauch rail |
| US20120060674A1 (en) * | 2008-09-12 | 2012-03-15 | Raytheon Company | Composite reinforced missile rail |
| US20200200506A1 (en) * | 2018-02-07 | 2020-06-25 | Raytheon Company | Rail-launching munition release |
| CN112665457A (en) * | 2020-12-17 | 2021-04-16 | 中国航空工业集团公司成都飞机设计研究所 | Pressurization launching device for airborne buried weapon |
| CN112696978A (en) * | 2020-12-24 | 2021-04-23 | 彩虹无人机科技有限公司 | Small missile ground launching height falling prevention method |
| CN218431747U (en) * | 2022-06-28 | 2023-02-03 | 湖南神州防务科技有限公司 | Airborne launcher and unmanned aerial vehicle system |
-
2023
- 2023-02-27 CN CN202310167396.8A patent/CN116101491B/en active Active
Patent Citations (8)
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|---|---|---|---|---|
| EP0284756A2 (en) * | 1987-04-01 | 1988-10-05 | Messerschmitt-Bölkow-Blohm Gesellschaft mit beschränkter Haftung | Aircraft mounting for a weapon |
| HK1007348A1 (en) * | 1991-08-08 | 1999-04-09 | Ml Aviat Ltd | Improved rail launcher for airborne missiles |
| EP2098814A1 (en) * | 2008-03-06 | 2009-09-09 | Saab Ab | A missile lauching system, and a hanger member for suspending the missile in a lauch rail |
| US20120060674A1 (en) * | 2008-09-12 | 2012-03-15 | Raytheon Company | Composite reinforced missile rail |
| US20200200506A1 (en) * | 2018-02-07 | 2020-06-25 | Raytheon Company | Rail-launching munition release |
| CN112665457A (en) * | 2020-12-17 | 2021-04-16 | 中国航空工业集团公司成都飞机设计研究所 | Pressurization launching device for airborne buried weapon |
| CN112696978A (en) * | 2020-12-24 | 2021-04-23 | 彩虹无人机科技有限公司 | Small missile ground launching height falling prevention method |
| CN218431747U (en) * | 2022-06-28 | 2023-02-03 | 湖南神州防务科技有限公司 | Airborne launcher and unmanned aerial vehicle system |
Non-Patent Citations (1)
| Title |
|---|
| 陈余军等: "舰载导弹垂直弹射出筒姿态影响因素分析", 弹箭与制导学报, vol. 31, no. 3, pages 69 - 72 * |
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|---|---|
| CN116101491B (en) | 2023-12-01 |
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