End effector, lock or jettison device for airborne missile fairing and method thereof

Abstract

The application discloses an end actuator, locking or throwing device and method for an airborne missile fairing, and belongs to the technical field of airborne missile fairings. The end actuator comprises a motor, the output ends of the motor at two ends are connected with a first speed reducer and a second speed reducer respectively, the second speed reducer is connected with a second output shaft, the first speed reducer is connected with a first output assembly, and the first output assembly is used for locking / unlocking the end pin of the fairing. The second output shaft is matched with a plurality of side locking mechanisms to realize the locking / unlocking of a plurality of points on the side of the fairing. The locking or throwing device for the airborne missile fairing comprises a throwing guide mechanism, a side locking mechanism and an end actuator. The end actuator for the airborne missile fairing is single, the multi-point locking mode is adopted, all the locking mechanisms have self-locking capability, and the device is safe and reliable.

Description

Technical Field

[0001] This invention relates to the field of aircraft door opening and closing technology, specifically to end actuators, locking or jettisoning devices and methods for airborne missile fairings. Background Technology

[0002] Internal weapons bays offer significant advantages in improving fighter jet stealth performance and optimizing aerodynamic design, but they also suffer from drawbacks such as design complexity, space occupation, impact on aerodynamic changes, and limited ammunition loading. While externally mounted missiles offer flexibility and ease of use, they have certain disadvantages in terms of aerodynamic drag and stealth performance. Using a fairing to enclose externally mounted missiles can effectively solve these aerodynamic drag and stealth problems. When the fighter jet needs to engage a target, it can jettison the fairing and then launch the missile. Currently, fairing connections often use explosive bolts; when the fairing separates, the explosive bolts disconnect, achieving separation. However, for airborne missile fairings, because the fairing is close to the missile, the explosive bolts may generate fragments that could damage the missile during operation. To address this, this invention provides a mechanical locking / jet-off method with advantages such as reusability and convenient installation. Summary of the Invention

[0003] This invention aims to solve the problems existing in the prior art and provides an end effector, locking or jettisoning device and method for airborne missile fairings. It adopts a single end effector for airborne missile fairings, a multi-point locking method, and all locking mechanisms have self-locking capability, making it safe and reliable.

[0004] The objective of this invention is achieved through the following technical solution:

[0005] An end actuator for an airborne missile fairing includes a motor. The output ends of the motor are connected to a first reducer and a second reducer, respectively. The second reducer is connected to a second output shaft. The first reducer is connected to a first output assembly. The first output assembly is used to lock / unlock the end pin of the fairing. The second output shaft cooperates with multiple side locking mechanisms to achieve multi-point locking / unlocking of the fairing sides.

[0006] Preferably, the motor, the first reducer, the second reducer, the second output shaft, and the first output assembly are all disposed inside the housing.

[0007] Preferably, the housing is provided with a cover near the first output component, and the cover is provided with a limiting groove.

[0008] Preferably, the first output component includes a first output shaft and a slider. A drive rod is provided at the upper end of the slider, and a drive groove is provided on the first output shaft. The drive rod passes through the limiting groove and is slidably disposed within the drive groove. First connecting rods are rotatably disposed on both sides of the slider. The other end of the first connecting rod is rotatably connected to a second connecting rod. A clamping block is provided at the location of the second connecting rod away from the first connecting rod. The first output shaft realizes the transformation of rotational motion into linear motion of the slider under the action of the drive groove and the limiting groove. The slider moves downward, causing the two second connecting rods to open. The slider moves upward, causing the two second connecting rods to close.

[0009] Preferably, the lower end of the slider is provided with a ejector pin, and the lower end of the cover is provided with an ejector pin groove that matches the ejector pin. When the slider moves downward, the ejector pin moves downward at the same time, and the lower end of the ejector pin passes through the ejector pin groove and pushes out the end pin of the fairing.

[0010] Preferably, the outer surface of the housing is provided with multiple mounting interfaces. These mounting interfaces are evenly distributed along the circumference of the housing. The mounting interfaces cooperate with the aircraft to allow the airborne missile fairing to be fixed to the aircraft using end actuators.

[0011] The airborne missile fairing locking or jettisoning device includes a jettisoning guidance mechanism, a side locking mechanism, and the aforementioned end actuator. The end actuator provides rotational power output to the side locking mechanism to achieve multi-point locking / unlocking of the fairing side and simultaneously locks / unlocks the fairing end pin. When unlocking, it assists in opening the fairing end pin, allowing high-speed airflow to enter the fairing. Under the action of the jettisoning guidance mechanism, the fairing rotates around the axis of the jettisoning guidance mechanism. When it rotates to a certain angle, it will detach from the fuselage under the action of wind resistance and gravity, thus realizing the jettisoning function.

[0012] Preferably, the second output shaft of the end effector is connected to multiple rotating links, adjacent rotating links are connected by universal joints, and each rotating link is provided with a side locking mechanism in the middle.

[0013] Preferably, the side locking mechanism includes two third links, one end of which is rotatably connected to a rotating link, and the other end of which is rotatably connected to a locking hook and a fixing seat; the fairing is provided with a locking element that matches the locking hook; the fixing seat is installed on the fuselage for fixing the locking hook so that the locking hook can complete the locking / unlocking action within the fixing seat.

[0014] Preferably, the launching and guiding mechanism includes a U-shaped slot at the tail of the fairing and a rotating shaft fixed to the fuselage.

[0015] The locking or jettisoning method for airborne missile fairings adopts the aforementioned locking or jettisoning device for airborne missile fairings;

[0016] The locking method is as follows: The fairing needs to be manually installed and locked. First, the U-shaped slot at the tail of the fairing is inserted into the rotating shaft of the fuselage. The fairing is rotated by the rotating shaft, causing the fairing end pin to move closer to the end actuator. This drives the end actuator to move, causing the slider to move upward. At this time, the two second linkages will close together with the fairing end pin, thus locking the fairing end pin. At the same time, the end actuator will drive the second output shaft to rotate, realizing the side locking mechanism locking the fairing side at multiple points.

[0017] The release method is as follows: the flight controller sends a drive command to the end effector, the motor drives the end effector to move, causing the slider to move downward. The pin at the lower end of the slider pushes the fairing end pin outward. At the same time, the two second linkages open together under the action of the slider, realizing the unlocking of the fairing end pin. While the end effector is actuating, it will drive the second output shaft to rotate, realizing the unlocking of the side locking mechanism at multiple points on the side of the fairing. After the fairing is unlocked, under the action of high-speed airflow, the U-shaped slot at the tail of the fairing rotates around the rotating shaft fixed to the fuselage. At the same time, the two sides of the tail of the fairing cover contact the fuselage, and its left and right deflection is restricted. When the fairing rotates to a certain angle, the fairing separates from the fuselage.

[0018] The beneficial effects of this technical solution are as follows:

[0019] I. The end actuator for an airborne missile fairing provided by the present invention is driven by a single motor. The first output component is used to lock / unlock the end pin of the fairing; the second output shaft cooperates with multiple side locking mechanisms to realize multi-point locking / unlocking of the fairing side.

[0020] II. The airborne missile fairing locking or jettisoning device provided by the present invention adopts a single airborne missile fairing end actuator and a multi-point locking method. All locking mechanisms have self-locking capability, making it safe and reliable.

[0021] Third, the locking or dropping method for airborne missile fairings provided by this invention has the advantages of reusability and convenient installation. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the installation of the airborne missile fairing in this invention;

[0023] Figure 2 This is a diagram showing the deployment of the airborne missile fairing in this invention;

[0024] Figure 3 This is a schematic diagram of the locking or ejection device for the airborne missile fairing in this invention;

[0025] Figure 4 This is a schematic diagram of the end effector for the airborne missile fairing in this invention. Figure 1 ;

[0026] Figure 5 This is a schematic diagram of the end effector for the airborne missile fairing in this invention. Figure 2 ;

[0027] Figure 6 This is a schematic diagram of the structure of the first output component of the end effector for the airborne missile fairing in this invention. Figure 1 ;

[0028] Figure 7 This is a schematic diagram of the structure of the first output component of the end effector for the airborne missile fairing in this invention. Figure 2 ;

[0029] Figure 8 This is a schematic diagram of the unlocking process of the end pin of the airborne missile fairing in this invention;

[0030] Figure 9 This is a schematic diagram of the unlocking process of the side pin of the airborne missile fairing in this invention;

[0031] Figure 10 This is a schematic diagram of the throwing and guiding mechanism in this invention;

[0032] Wherein: 100, end actuator; 110, motor; 120, first reducer; 130, second reducer; 140, second output shaft; 150, first output assembly; 151, cover; 152, limiting slide groove; 153, first output shaft; 154, slider; 155, drive rod; 156, drive slide groove; 158, first connecting rod; 159, second connecting rod; 1510, clamping block; 1511, ejector pin; 1512, ejector pin groove; 160, side locking mechanism; 161, third connecting rod; 162, locking hook; 163, fixed base; 170, housing; 180, mounting interface; 200, throwing guide mechanism; 210, U-shaped slot; 220, rotating shaft; 300, fairing; 310, locking element; 320, fairing end pin; 400, rotating connecting rod; 500, universal joint. Detailed Implementation

[0033] The present invention will be further described in detail below with reference to embodiments, but the implementation of the present invention is not limited thereto.

[0034] Example 1

[0035] like Figures 4-7As shown, this embodiment provides an end actuator for an airborne missile fairing, including a motor 110. The output ends of the motor 110 are respectively connected to a first reducer 120 and a second reducer 130. The second reducer 130 is connected to a second output shaft 140. The first reducer 120 is connected to a first output component 150. The first output component 150 is used to lock / unlock the fairing end pin 320. The second output shaft 140 cooperates with multiple side locking mechanisms 160 to realize multi-point locking / unlocking of the fairing 300 side.

[0036] Example 2

[0037] like Figures 4-7 As shown, this embodiment provides an end actuator for an airborne missile fairing, including a motor 110. The output ends of the motor 110 are respectively connected to a first reducer 120 and a second reducer 130. The second reducer 130 is connected to a second output shaft 140. The first reducer 120 is connected to a first output component 150. The first output component 150 is used to lock / unlock the fairing end pin 320. The second output shaft 140 cooperates with multiple side locking mechanisms 160 to realize multi-point locking / unlocking of the fairing 300 side.

[0038] The motor 110, the first reducer 120, the second reducer 130, the second output shaft 140, and the first output assembly 150 are all disposed inside the housing 170.

[0039] The housing 170 is provided with a cover 151 near the first output component 150, and the cover 151 is provided with a limiting groove 152.

[0040] The first output component 150 includes a first output shaft 153 and a slider 154. A drive rod 155 is provided at the upper end of the slider 154. A drive groove 156 is provided on the first output shaft 153. The drive rod 155 passes through the limiting groove 152 and is slidably disposed in the drive groove 156. First connecting rods 158 are rotatably disposed on both sides of the slider 154. The other end of the first connecting rod 158 is rotatably connected to a second connecting rod 159. A clamping block 1510 is provided on the second connecting rod 159 away from the first connecting rod 158. The rotational motion of the first output shaft 153 is converted into the linear motion of the slider 154 by the action of the drive groove 156 and the limiting groove 152. The slider 154 moves downward, causing the two second connecting rods 159 to open. The slider 154 moves upward, causing the two second connecting rods 159 to close.

[0041] The slider 154 is provided with a ejector pin 1511 at its lower end, and the cover 151 is provided with an ejector pin groove 1512 that matches the ejector pin 1511 at its lower end. When the slider 154 moves downward, the ejector pin 1511 moves downward at the same time, and the lower end of the ejector pin 1511 passes through the ejector pin groove 1512 and pushes out the fairing end pin 320.

[0042] The housing 170 has multiple mounting interfaces 180 on its exterior. These mounting interfaces 180 are evenly distributed around the circumference of the housing 170. The mounting interfaces 180 cooperate with the aircraft to secure the airborne missile fairing 300 to the aircraft using end effectors 100.

[0043] Example 3

[0044] like Figures 1-10 As shown, the airborne missile fairing locking or jettisoning device includes a jettisoning guidance mechanism 200, a side locking mechanism 160, and an end actuator 100 as described in Embodiment 2. The end actuator 100 provides rotational power output to the side locking mechanism 160 to achieve multi-point locking / unlocking of the fairing 300's side and simultaneously locks / unlocks the fairing end pin 320. When unlocking, it assists in opening the fairing end pin 320, allowing high-speed airflow to enter the interior of the fairing 300. Under the action of the jettisoning guidance mechanism 200, the fairing 300 rotates around the axis of the jettisoning guidance mechanism 200. When it rotates to a certain angle, it will detach from the fuselage under the action of wind resistance and gravity, thus realizing the jettisoning function.

[0045] The second output shaft 140 of the end actuator 100 is connected to a plurality of rotating links 400. Adjacent rotating links 400 are connected by universal joints 500. Each rotating link 400 is provided with a side locking mechanism 160 in the middle.

[0046] The side locking mechanism 160 includes two third links 161. One end of the third link 161 is rotatably connected to the rotating link 400, and the other end of the third link 161 is rotatably connected to a locking hook 162 and a fixing seat 163. The fairing 300 is provided with a locking element 310 that matches the locking hook 162. The fixing seat 163 is installed on the machine body and is used to fix the locking hook 162 so that the locking hook 162 can complete the locking / unlocking action within the fixing seat 163.

[0047] The launching and guiding mechanism 200 includes a U-shaped slot 210 at the tail of the fairing 300 and a rotating shaft 220 fixed to the fuselage.

[0048] Example 4

[0049] like Figures 1-10 As shown, the locking or jettisoning method for the airborne missile fairing adopts the locking or jettisoning device for the airborne missile fairing described in Example 3.

[0050] The locking method is as follows: The fairing 300 needs to be manually installed and locked. First, the U-shaped slot 210 at the tail of the fairing 300 is inserted into the rotating shaft 220 of the fuselage. The fairing 300 is rotated by the rotating shaft 220, causing the fairing end pin 320 to move closer to the end actuator 100. This drives the end actuator 100 to move, causing the slider 154 to move upward. At this time, the two second connecting rods 159 will close together with the fairing end pin 320, thus locking the fairing end pin 320. At the same time, the end actuator 100 will drive the second output shaft 140 to rotate, thus locking the side of the fairing 300 at multiple points by the side locking mechanism 160.

[0051] The release method is as follows: the flight controller sends a drive command to the end effector 100, the motor 110 drives the end effector 100 to move, causing the slider 154 to move downward. The pin 1511 at the lower end of the slider 154 will push the fairing end pin 320 outward. At the same time, the two second connecting rods 159 will open together under the action of the slider 154, realizing the unlocking of the fairing end pin 320. When the end effector 100 is actuated, it will drive the second output shaft 140 to rotate, realizing the unlocking of the side locking mechanism 160 at multiple points on the side of the fairing 300. After the fairing 300 is unlocked, under the action of high-speed airflow, the U-shaped slot 210 at the tail of the fairing 300 rotates around the rotating shaft 220 fixed to the fuselage. At the same time, the two sides of the tail of the fairing 300 are in contact with the fuselage, and its left and right deflection is restricted. When the fairing 300 rotates to a certain angle, the fairing 300 separates from the fuselage.

[0052] The beneficial effects of this technical solution are as follows:

[0053] I. The end actuator 100 for the airborne missile fairing 300 provided by the present invention is driven by a single motor 110. The first output component 150 is used to lock / unlock the fairing end pin 320; the second output shaft 140 cooperates with multiple side locking mechanisms 160 to realize multi-point locking / unlocking of the fairing 300 side.

[0054] II. The airborne missile fairing 300 locking or launching device provided by the present invention adopts a single airborne missile fairing 300 end actuator 100 and a multi-point locking method. All locking mechanisms have self-locking capability, which is safe and reliable.

[0055] Third, the airborne missile fairing 300 provided by this invention has the advantages of being reusable and easy to install.

[0056] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. An end effector for an airborne missile fairing, characterized in that: The system includes a motor (110), the output ends of which are connected to a first reducer (120) and a second reducer (130) respectively. The second reducer (130) is connected to a second output shaft (140), and the first reducer (120) is connected to a first output assembly (150). The first output assembly (150) is used to lock / unlock the fairing end pin (320). The second output shaft (140) cooperates with multiple side locking mechanisms (160) to achieve multi-point locking / unlocking of the fairing (300) side. The motor (110), the first reducer (120), the second reducer (130), the second output shaft (140), and the first output assembly (150) are all disposed inside the housing (170); The housing (170) is provided with a cover (151) near the first output component (150), and the cover (151) is provided with a limit groove (152). The first output component (150) includes a first output shaft (153) and a slider (154). A drive rod (155) is provided at the upper end of the slider (154), and a drive groove (156) is provided on the first output shaft (153). The drive rod (155) passes through the limiting groove (152) and is slidably disposed in the drive groove (156). The slider (154) is rotatably provided with first connecting rods (158) on both sides. The other end of the first connecting rod (158) is rotatably connected to the second connecting rod (159). A clamping block (1510) is provided on the second connecting rod (159) away from the first connecting rod (158). The first output shaft (153) realizes the transformation of the rotational motion into the linear motion of the slider (154) through the action of the drive slide groove (156) and the limiting slide groove (152). When the slider (154) moves downward, it causes the two second connecting rods (159) to open. When the slider (154) moves upward, it causes the two second connecting rods (159) to close.

2. The end effector for an airborne missile fairing according to claim 1, characterized in that: The lower end of the slider (154) is provided with a push pin (1511), and the lower end of the cover (151) is provided with a push pin groove (1512) that matches the push pin (1511). When the slider (154) moves downward, the push pin (1511) moves downward at the same time. After the lower end of the push pin (1511) passes through the push pin groove (1512), it pushes out the fairing end pin (320).

3. The end effector for an airborne missile fairing according to claim 2, characterized in that: The housing (170) has multiple mounting interfaces (180) on its exterior; the mounting interfaces (180) cooperate with the aircraft to fix the airborne missile fairing (300) to the aircraft using end effectors (100).

4. A locking or jettisoning device for an airborne missile fairing, characterized in that: The system includes a jettisoning guidance mechanism (200), a side locking mechanism (160), and an end actuator (100) for an airborne missile fairing as described in any one of claims 1-3. The end actuator (100) provides rotational power output to the side locking mechanism (160) to achieve multi-point locking / unlocking of the fairing (300) side and simultaneously locks / unlocks the fairing end pin (320). When unlocking, it assists in opening the fairing end pin (320) to allow high-speed airflow into the interior of the fairing (300). Under the action of the jettisoning guidance mechanism (200), the fairing (300) rotates around the axis of the jettisoning guidance mechanism (200). When it rotates to a certain angle, it will detach from the fuselage under the action of wind resistance and gravity, thus realizing the jettisoning function.

5. The locking or jettisoning device for an airborne missile fairing according to claim 4, characterized in that: The second output shaft (140) of the end actuator (100) is connected to a plurality of rotating links (400), adjacent rotating links (400) are connected by universal joints (500), and each rotating link (400) is provided with a side locking mechanism (160) in the middle.

6. The locking or jettisoning device for an airborne missile fairing according to claim 5, characterized in that: The side locking mechanism (160) also includes two third links (161). One end of the third link (161) is rotatably connected to the rotating link (400), and the other end of the third link (161) is rotatably connected to a locking hook (162) and a fixed seat (163). The fairing (300) is provided with a locking element (310) that matches the locking hook (162). The fixed seat (163) is installed on the fuselage and is used to fix the locking hook (162) so that the locking hook (162) can complete the locking / unlocking action in the fixed seat (163).

7. The locking or jettisoning device for an airborne missile fairing according to claim 6, characterized in that: The launching guide mechanism (200) includes a U-shaped slot (210) at the tail of the fairing (300) and a rotating shaft (220) fixed to the fuselage.

8. A locking or jettisoning method for an airborne missile fairing, characterized in that, Use the locking or jettisoning device for airborne missile fairings as described in any one of claims 4-7; The locking method is as follows: The fairing (300) is manually installed and locked: First, the U-shaped slot (210) at the tail of the fairing (300) is inserted into the rotating shaft (220) of the fuselage. The fairing (300) is rotated by the rotating shaft (220) so that the fairing end pin (320) moves closer to the end actuator (100), driving the end actuator (100) to move and the slider (154) to move upward. At this time, the two second connecting rods (159) will close together with the fairing end pin (320) to lock the fairing end pin (320). At the same time, the end actuator (100) will drive the second output shaft (140) to rotate, so that the side locking mechanism (160) locks the fairing (300) at multiple points on the side. The launching method is as follows: the flight controller sends a drive command to the end effector (100), the motor (110) drives the end effector (100) to move, causing the slider (154) to move downward. The pin (1511) at the lower end of the slider (154) will push the fairing end pin (320) outward. At the same time, the two second linkages (159) will open together under the action of the slider (154), thereby unlocking the fairing end pin (320). The end effector (100) will drive the second linkages (159) to move outward. The output shaft (140) rotates to unlock the side of the fairing (300) at multiple points using the side locking mechanism (160). After the fairing (300) is unlocked, under the action of high-speed airflow, the U-shaped slot (210) at the tail of the fairing (300) rotates around the rotating shaft (220) fixed to the fuselage. At the same time, the two sides of the tail of the fairing (300) come into contact with the fuselage, and its left and right deflection is restricted. When the fairing (300) rotates to a certain angle, the fairing (300) separates from the fuselage.

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