A launch tower outer counter support arm

Abstract

The application relates to a launching platform outside-inverted supporting arm which comprises a supporting arm body and an actuating cylinder arranged on the left side of the supporting arm body, the lower end of the supporting arm body is hinged to a first support fixed on a launching platform frame through a first pin shaft, the actuating cylinder comprises a cylinder body, the lower end of the cylinder body is hinged to a second support fixed on the launching platform frame through a second pin shaft, a piston is arranged in the cylinder body, the piston is coaxially fixed with a piston rod which extends out of the upper end of the cylinder body, the piston rod is hinged to a third support fixed on the middle part of the left side of the supporting arm body through a third pin shaft, a rubber shock absorber is arranged in the cylinder body below the piston, the rubber shock absorber is provided with an air hole which penetrates the rubber shock absorber from top to bottom, the air hole is connected with a gas charging and discharging channel, and a reset spring is arranged in the cylinder body above the piston and sleeved on the piston rod. The supporting arm has the advantages of simple structure, convenient control, sensitive action, safety and reliability and strong practicability.

Description

Technical Field

[0001] The invention relates to a supporting device, in particular to an outward-folding supporting arm for a launching platform. Background Art

[0002] In the aerospace field, a launch pad is a comprehensive device used to support aircraft and complete test and launch processes such as refueling and launch. The launch pad mainly includes a launch platform and multiple support arms installed on the launch platform. The aircraft is supported by multiple support arms, and the multiple support arms correspond to the support points set around the bottom of the aircraft. Traditional launch pad support arms are usually fixed and cannot complete the outward tilting action. For aircraft with a large frontal area, there will be a certain amount of lateral drift during ignition and takeoff, which may cause interference and collision with the support arms, affecting safety. Summary of the Invention

[0003] The purpose of the present invention is to provide a launch platform outward-folding support arm, which has the advantages of simple structure, convenient operation, sensitive movement, safety, reliability and strong practicality.

[0004] In order to solve the above-mentioned problems existing in the prior art, the present invention provides an outward-folding support arm of a launch platform, comprising an arm body and an actuator cylinder located on the left side of the arm body, the lower end of the arm body being hinged to a first support fixed on the launch platform through a first pin shaft, the actuator cylinder comprising a cylinder body, the lower end of the cylinder body being hinged to a second support fixed on the launch platform through a second pin shaft, a piston being provided in the cylinder body, a piston rod being coaxially fixed with the piston extending out of the upper end of the cylinder body, the piston rod being hinged to a third support fixed on the middle part of the left side of the arm body through a third pin shaft, a rubber shock absorber being provided on the lower side of the piston in the cylinder body, the rubber shock absorber being provided with an air vent which passes through the upper and lower parts, the air vent being connected to an air charging and discharging channel, a return spring being provided on the piston rod in the cylinder body on the upper side of the piston.

[0005] Furthermore, the present invention provides an outward-folding support arm for a launch platform, wherein the rubber shock absorber includes a rubber body, an outer wall of the rubber body is provided with annular grooves spaced apart in an upper and lower direction, the notch width of the annular grooves is greater than the width of the groove bottom, and the rubber body is provided with support rings alternately distributed with the annular grooves in the upper and lower directions, and the outer edge thickness of the support rings is less than the inner edge thickness.

[0006] Furthermore, the present invention provides an outward-folding support arm of a launch platform, wherein the piston rod is provided with a sleeve that slides together with the piston rod, a retaining ring is provided on the outer wall of the sleeve, and two return springs are provided, the upper and lower ends of the upper return spring correspondingly press on the cylinder and the retaining ring, and the upper and lower ends of the lower return spring correspondingly press on the retaining ring and the piston.

[0007] Furthermore, the present invention provides an outward-folding support arm of a launch platform, wherein the barrel includes a cylinder and an upper barrel cap and a lower barrel cap screwed onto the upper and lower ends of the cylinder through threads, a sealing ring is provided between the lower barrel cap and the cylinder, and a lower support ear hinged to the second support is provided at the bottom of the lower barrel cap, the piston rod passes through the upper barrel cap and makes the two slide together, and the end of the piston rod is provided with an upper support ear hinged to the third support.

[0008] Furthermore, the present invention provides an outward-folding support arm for a launch platform, wherein the lower support ear is provided with an axial hole for installing a second pin shaft, the inner wall of the axial hole is provided with a first air channel connected to the air vent, the second pin shaft is provided with an annular air groove along the circumferential direction at a position corresponding to the first air channel, sealing rings are respectively installed on the second pin shaft on both sides of the annular air groove through sealing grooves, an inflation head is installed at one end of the second pin shaft, and the inflation head is connected to the annular air groove through a second air channel provided in the second pin shaft, and the inflation and discharge air channel refers to a channel formed by the first air channel, the annular air groove, the second air channel and the inflation head being connected in sequence.

[0009] Furthermore, the present invention provides an outward-folding support arm for a launch platform, wherein the lower half of the arm body is a cavity structure that passes through from left to right, a limit baffle fixedly connected to the front and rear side walls is provided in the cavity, and the first support is provided with a limit block located on the right side of the limit baffle; after the arm body is erected into position, the limit baffle is fitted with the limit block.

[0010] Furthermore, the present invention provides an outward-folding support arm for a launch platform, wherein a support platform is provided on the top of the arm body, a support plate is fixed on the support platform by screws, the support plate is provided with an ear plate extending to the right, a pull rod pad supporting the aircraft is rotated through a threaded hole on the ear plate, and the pull rod pad is provided with a light hole for installing a windproof pull rod.

[0011] Furthermore, the present invention provides an external-folding support arm of a launch platform, wherein the piston includes a main body and a first guide sleeve fixed on the outside of the main body, the first guide sleeve is slidably fitted with the cylinder, a sealing ring is installed on the outer wall of the first guide sleeve, a second guide sleeve is fixed in the through hole on the top of the upper cylinder cap, and the piston rod passes through the second guide sleeve and makes the two slidably fitted.

[0012] Furthermore, the present invention provides an outward-folding support arm for a launch platform, wherein a pressure plate is fixed to the top of the upper tube cap by screws, a sealing gasket that fits the piston rod is clamped between the pressure plate and the upper tube cap, and an air hole is provided on the peripheral wall of the upper tube cap.

[0013] Furthermore, the present invention provides an outward-folding support arm for a launch platform, wherein the piston and the upper cylinder cap are respectively provided with annular grooves for clamping a reset spring.

[0014] Compared with the prior art, the present invention has the following advantages: the present invention provides an arm body and an actuator cylinder located on the left side of the arm body, so that the lower end of the arm body is hinged to a first support fixed to the launch platform frame via a first pin, the actuator cylinder is provided with a cylinder body, so that the lower end of the cylinder body is hinged to a second support fixed to the launch platform frame via a second pin, a piston is provided in the cylinder body, a piston rod extending from the upper end of the cylinder body is coaxially fixed to the piston, and the piston rod is hinged to a third support fixed to the middle portion of the left side of the arm body via a third pin, a rubber shock absorber is provided in the cylinder body below the piston, a vent hole extending vertically through the rubber shock absorber is provided, the vent hole is connected to the charging and discharging passages, and a return spring is provided in the cylinder body above the piston, which is sleeved on the piston rod. Thus, a launch platform tilting support arm is formed that is simple in structure, easy to operate, sensitive in operation, safe and reliable, and highly practical. In practical applications, multiple support arms are positioned on the launch platform corresponding to the positions of the aircraft's support points, with the actuator positioned outboard of the support arms relative to the common center of the multiple support arms. Before placing the aircraft, the actuator is inflated through the air charging and discharging channels and the vent holes of the rubber shock absorber. This allows the piston to compress the return spring, extending the piston rod and raising the support arms. The aircraft is then placed on the multiple support arms. Immediately prior to ignition, the actuator is deflated through the air charging and discharging channels and the vent holes of the rubber shock absorber. During ignition and takeoff, the piston rod rapidly retracts under the action of the return spring, driving the support arms outward and away from the aircraft, creating the safe distance required for lateral drift of the aircraft. This prevents interference and collision between the aircraft and the support arms, thereby improving safety. By placing the rubber shock absorber on the underside of the piston in the actuator, the present invention provides a buffering function, preventing damage to the actuator due to impact, and reduces rebound, ensuring the effectiveness and reliability of the support arm outward tilt.

[0015] The following is a further detailed description of a launch platform outward-folding support arm of the present invention in conjunction with the specific embodiments shown in the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a front view of an outward-folding support arm of a launch platform according to the present invention;

[0017] Figure 2 This is a left side view of an outward-folding support arm of a launch platform according to the present invention;

[0018] Figure 3 This is an axonometric view of an outward-folding support arm of a launch platform according to the present invention;

[0019] Figure 4 for Figure 1 AA view in the;

[0020] Figure 5 for Figure 2BB view in the figure;

[0021] Figure 6 This is a state diagram of a launch platform outward-folding support arm of the present invention when it is outward-folding;

[0022] Figure 7 This is a front view of an actuator in an outward-folding support arm of a launch platform according to the present invention;

[0023] Figure 8 for Figure 7 CC view in the figure;

[0024] Figure 9 The figure is a cross-sectional view of a rubber shock absorber in an outward-folding support arm of a launch platform according to the present invention. DETAILED DESCRIPTION

[0025] First of all, it should be noted that the directional words such as up, down, left, right, front and back mentioned in the present invention are only described according to the drawings for the convenience of understanding, and are not intended to limit the technical solution and scope of protection of the present invention.

[0026] like Figures 1 to 9 The embodiment of the present invention, a launch platform external tilt support arm, includes an arm body 1 and an actuator 2 located on the left side of the arm body 1. The lower end of the arm body 1 is hinged to a first support 4 fixed to the launch platform frame via a first pin 3. The actuator 2 is provided with a cylinder body 21, and the lower end of the cylinder body 21 is hinged to a second support 6 fixed to the launch platform frame via a second pin 5. A piston 22 is provided in the cylinder body 21, and a piston rod 23 extending from the upper end of the cylinder body 21 is coaxially fixed to the piston 22. The piston rod 23 is hinged to a third support 8 fixed to the middle of the left side of the arm body 1 via a third pin 7. A rubber shock absorber 24 is provided in the cylinder body 21 below the piston 22. A vent hole 241 extending vertically through the rubber shock absorber 24 is provided, and the vent hole 241 is connected to the air charging and discharging passages. A return spring 25 is provided in the cylinder body 21 above the piston 22, and is sleeved on the piston rod 23.

[0027] The above structure constitutes a launch platform outer-falling type supporting arm which is simple in structure, convenient to operate, sensitive in action, safe and reliable, and practical. In actual application, according to the supporting point position of the aircraft, a plurality of supporting arms are correspondingly arranged on the launch platform, wherein the actuating cylinder 2 is located at the outer side of the common center of the plurality of supporting arms, i.e. the actuating cylinder 2 is located at the side away from the aircraft. Before placing the aircraft, the actuating cylinder 2 is inflated through the inflation and deflation channel and the air vent hole 241 of the rubber shock absorber 24, so as to compress the return spring 25 through the piston 22, make the piston rod 23 extend and erect the supporting arm body 1, then place the aircraft on the plurality of supporting arm bodies 1, deflate the actuating cylinder 2 through the inflation and deflation channel and the air vent hole 241 of the rubber shock absorber 24 before ignition and launch, and under the action of the return spring 25, the piston rod 23 will be quickly recovered and drive the supporting arm body 1 to fall outward to be away from the aircraft, so as to leave a safe distance required by the lateral drift of the aircraft, which can avoid the interference and collision between the aircraft and the supporting arm body 1, and improve the safety. The rubber shock absorber 24 is arranged at the lower side of the piston 22, which can realize the buffering function, prevent the damage of the impact to the actuating cylinder 2, reduce the rebound amount, and ensure the effectiveness and reliability of the outward falling of the supporting arm body 1. It should be noted that according to the supporting point position of the aircraft, the plurality of supporting arms are usually distributed along the circumference of the aircraft to provide stable support; the actuating cylinder 2 is located at the left side of the supporting arm body 1 according to the description of the drawings, and according to the position of the plurality of supporting arms relative to the aircraft, the left side means that the actuating cylinder 2 is located at the side away from the aircraft. In actual application, in order to ensure that the supporting arm body 1 can still support the aircraft after the actuating cylinder 2 is deflated, a left-right through cavity structure is arranged in the lower half of the supporting arm body 1, a limiting baffle 11 fixedly connected with the front and rear side walls is arranged in the cavity, a limiting block 41 is arranged on the first support 4 and located at the right side of the limiting baffle 11, and the limiting baffle 11 is attached to the limiting block 41 after the supporting arm body 1 is erected in place. After the actuating cylinder 2 is deflated, the supporting arm body 1 can still stably support the aircraft through the blocking of the limiting block 41 to the limiting baffle 11 and the gravity of the aircraft.

[0028] As an optimization solution, this specific embodiment adopts the following structure for the rubber shock absorber 24: a rubber body 242 is provided, and annular grooves 243 are provided on the outer wall of the rubber body 242 at intervals, with the notch width of the annular grooves 243 being greater than the width of the groove bottom. Furthermore, support rings 244 are provided in the rubber body 242, with the support rings 244 and annular grooves 243 alternately arranged in the vertical direction, and the outer edge thickness of the support rings 244 being less than the inner edge thickness. This structure improves the cushioning performance of the rubber shock absorber 24 through the annular grooves 243, and increases the strength of the rubber shock absorber 24 through the support rings 244. The alternating arrangement of the annular grooves 243 and the support rings 244 enhances the cushioning effect of the rubber shock absorber 24, reduces the rebound force of the rubber shock absorber 24, further ensures the effectiveness and reliability of the outward tilt of the support arm body 1, and enhances safety and reliability. As an optimization solution, this specific embodiment includes a sleeve 231 that slides over the piston rod 23, a retaining ring 232 on the outer wall of the sleeve 231, and two return springs 25. The upper and lower ends of the upper return spring 25 press against the cylinder 21 and the retaining ring 232, respectively, while the upper and lower ends of the lower return spring 25 press against the retaining ring 232 and the piston 22. Compared to a single-spring structure, this structural arrangement reduces manufacturing difficulty while improving reset capability and actuation sensitivity. Furthermore, the sliding of the sleeve 231 allows the two return springs 25 to operate synchronously, enhancing adaptability.

[0029] As a specific embodiment, the present invention provides a split structure for the barrel 21: comprising a cylinder 211, an upper barrel cap 212, and a lower barrel cap 213 threadedly mounted on the upper and lower ends of the cylinder 211, respectively. A sealing ring is provided between the lower barrel cap 213 and the cylinder 211, and a lower lug 214 hingedly connected to the second support 6 is provided at the bottom of the lower barrel cap 213. The piston rod 23 passes through the upper barrel cap 212 and slides therethrough. An upper lug 233 hingedly connected to the third support 8 is provided at the end of the piston rod 23. This configuration of the barrel 21 has the characteristics of a simple structure and easy assembly and disassembly. As a specific embodiment, the present invention provides an axial hole 215 for mounting the second pin 5 on the lower lug 214. A first air passage 216 communicating with the vent 241 is provided on the inner wall of the axial hole 215. An annular air groove 51 is circumferentially provided on the second pin 5 at a position corresponding to the first air passage 216. Seal rings are installed on the second pin 5 on either side of the annular air groove 51 through sealing grooves 52. An inflation head 53 is installed at one end of the second pin 5, communicating with the annular air groove 51 through a second air passage 54 provided in the second pin 5. The aforementioned inflation and deflation passage refers to a passage formed by the sequential connection of the first air passage 216, the annular air groove 51, the second air passage 54, and the inflation head 53. This arrangement allows the actuator 2 to be inflated and deflated by connecting an inflation line and an air source to the inflation head 53, and allows for remote control operation to ensure personnel safety. As a specific embodiment, the present invention comprises a support platform 12 disposed at the top of the support arm 1. A support plate 13 is screwed to the support platform 12, and a lug 131 extending rightward is provided on the support plate 13. A tie rod pad 9 for supporting the aircraft is threaded through a threaded hole in the lug 131, and a light hole 91 is provided on the tie rod pad 9 for installing a windproof tie rod. This arrangement ensures structural and support stability through the support platform 12. The support plate 13 and lug 131 allow the support arm 1 to be positioned as far away from the aircraft as possible. The tie rod pad 9 reduces the contact area with the aircraft and allows for height adjustment. The light hole 91 provided in the tie rod pad 9, into which a windproof tie rod connected to the aircraft is installed, provides a secure and windproof function, preventing the aircraft from capsizing due to wind. It should be noted that the windproof tie rod, a threaded rod, between the aircraft and the tie rod pad 9 should be removed before ignition.

[0030] As a specific embodiment, the present invention provides the piston 22 with the following combined structure: it includes a main body 221 and a first guide sleeve 222 fixed to the outside of the main body 221, wherein the first guide sleeve 222 is slidably engaged with the cylinder barrel 211, and a sealing ring is mounted on the outer wall of the first guide sleeve 222. This arrangement reduces the difficulty of preparation and assembly, and the first guide sleeve 222 ensures the smooth movement of the piston 22. Simultaneously, this specific embodiment secures a second guide sleeve 2121 in the through hole at the top of the upper cylinder cap 212, allowing the piston rod 23 to pass through the second guide sleeve 2121 and slidably engage with the piston rod 23. This arrangement ensures the smooth movement of the piston rod 23 through the second guide sleeve 2121. As a specific embodiment, the present invention secures a pressure plate 2122 to the top of the upper cap 212 via screws. A sealing gasket 2123, which mates with the piston rod 23, is secured between the pressure plate 2122 and the upper cap 212 for protection. Furthermore, an air hole 2124 is provided on the peripheral wall of the upper cap 212 to prevent air holding from affecting the mobility of the actuator 2. To facilitate positioning of the return spring 25, an annular groove for the return spring 25 is provided on both the piston 22 and the upper cap 212, serving as a spring seat.

[0031] The above embodiments are merely descriptions of preferred implementations of the present invention and are not intended to limit the scope of protection claimed for the present invention. Without departing from the design concept of the present invention, various modifications made by those skilled in the art based on the technical solution of the present invention should fall within the scope of protection determined by the claims of the present invention.

Claims

1. A launch platform outward tilt support arm, characterized in that: The invention comprises an arm body (1) and an actuator cylinder (2) located on the left side of the arm body (1), wherein the lower end of the arm body (1) is hinged to a first support (4) fixed on the launch platform through a first pin shaft (3), and the actuator cylinder (2) comprises a cylinder body (21), wherein the lower end of the cylinder body (21) is hinged to a second support (6) fixed on the launch platform through a second pin shaft (5), and a piston (22) is provided in the cylinder body (21), and a piston rod (23) extending from the upper end of the cylinder body (21) is coaxially fixed to the piston (22), and the piston rod (23) is hinged to a third support (8) fixed on the middle part of the left side of the arm body (1) through a third pin shaft (7), and a piston rod (23) is provided in the cylinder body (21) on the lower side of the piston (22). A rubber shock absorber (24) is provided. The rubber shock absorber (24) is provided with an air vent (241) which passes through the upper and lower parts. The air vent (241) is connected to an air charging and discharging passage. A return spring (25) which is sleeved on the piston rod (23) is provided in the cylinder (21) on the upper side of the piston (22). The rubber shock absorber (24) comprises a rubber body (242). An annular groove (243) which is spaced apart from each other is provided on the outer wall of the rubber body (242). The notch width of the annular groove (243) is greater than the groove bottom width. A support ring (244) which is alternately distributed with the annular groove (243) in the upper and lower directions is provided in the rubber body (242). The outer edge thickness of the support ring (244) is less than the inner edge thickness.

2. The launch platform outward-folding support arm according to claim 1, characterized in that: The piston rod (23) is provided with a sleeve (231) that is slidably matched with the piston rod (23), and a retaining ring (232) is provided on the outer wall of the sleeve (231). Two return springs (25) are provided, and the upper and lower ends of the upper return spring (25) are pressed against the cylinder (21) and the retaining ring (232) respectively, and the upper and lower ends of the lower return spring (25) are pressed against the retaining ring (232) and the piston (22) respectively.

3. The launch platform outward-folding support arm according to claim 2, characterized in that: The barrel (21) comprises a cylinder (211) and an upper barrel cap (212) and a lower barrel cap (213) which are screwed onto the upper and lower ends of the cylinder (211) via threads. A sealing ring is provided between the lower barrel cap (213) and the cylinder (211). The bottom of the lower barrel cap (213) is provided with a lower support ear (214) which is hinged to the second support (6). The piston rod (23) passes through the upper barrel cap (212) and the two are slidably matched. The end of the piston rod (23) is provided with an upper support ear (233) which is hinged to the third support (8).

4. The launch platform outward-folding support arm according to claim 3, characterized in that: The lower support ear (214) is provided with an axial hole (215) for installing the second pin shaft (5), and the inner wall of the axial hole (215) is provided with a first air channel (216) connected to the vent hole (241). The second pin shaft (5) is provided with an annular air groove (51) along the circumferential direction at a position corresponding to the first air channel (216). The second pin shaft (5) on both sides of the annular air groove (51) is respectively provided with a sealing ring through a sealing groove (52). An inflation head (53) is installed at one end of the second pin shaft (5), and the inflation head (53) is connected to the annular air groove (51) through a second air channel (54) provided in the second pin shaft (5). The inflation and deflation channel refers to a channel formed by the first air channel (216), the annular air groove (51), the second air channel (54) and the inflation head (53) being connected in sequence.

5. The launch platform outward-folding support arm according to claim 4, characterized in that: The lower half of the support arm body (1) is a cavity structure that passes through from left to right, and a limit baffle (11) fixedly connected to the front and rear side walls is provided in the cavity. The first support (4) is provided with a limit block (41) located on the right side of the limit baffle (11); after the support arm body (1) is erected into position, the limit baffle (11) and the limit block (41) are in contact with each other.

6. The launch platform outward-folding support arm according to claim 5, characterized in that: A support platform (12) is provided on the top of the support arm body (1), a support plate (13) is fixed on the support platform (12) by screws, the support plate (13) is provided with an ear plate (131) extending to the right, a tie rod pad (9) for supporting the aircraft is rotated through a threaded hole on the ear plate (131), and the tie rod pad (9) is provided with a light hole (91) for installing a windproof tie rod.

7. The launch platform outward-folding support arm according to claim 6, characterized in that: The piston (22) comprises a main body (221) and a first guide sleeve (222) fixed on the outside of the main body (221); the first guide sleeve (222) is in sliding engagement with the cylinder (211); a sealing ring is mounted on the outer wall of the first guide sleeve (222); a second guide sleeve (2121) is fixed in the through hole at the top of the upper cylinder cap (212); the piston rod (23) passes through the second guide sleeve (2121) and the two are in sliding engagement.

8. The launch platform outward-folding support arm according to claim 7, characterized in that: A pressure plate (2122) is fixed to the top of the upper tube cap (212) by screws, a sealing gasket (2123) that fits the piston rod (23) is clamped between the pressure plate (2122) and the upper tube cap (212), and an air hole (2124) is provided on the peripheral wall of the upper tube cap (212).

9. The launch platform outward-folding support arm according to claim 8, characterized in that: The piston (22) and the upper cylinder cap (212) are respectively provided with annular grooves for clamping a return spring (25).

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