A triple redundant parachute cabin device for water rocket parachute recovery

Abstract

The present invention relates to a triple-redundancy parachute chamber device for parachute opening and recovery of a water rocket, comprising: a parachute chamber body (1), a parachute chamber door (2) installed on the parachute chamber body (1) and capable of being opened and closed, a parachute (3) connected to the parachute chamber door (2), an air pressure control switch (4) and a timing servo (5); the parachute chamber body (1) is provided with an ejection assembly (1a) for ejecting the parachute (3); the air pressure control switch (4) and the timing servo (5) are simultaneously connected to the parachute chamber door (2) for controlling the opening and closing of the parachute chamber door (2); when the parachute chamber door (2) is closed, the parachute (3) can be folded between the parachute chamber body (1) and the parachute chamber door (2); when the parachute chamber door (2) is opened, the ejection assembly (1a) ejects the parachute (3). The parachute opening redundancy of the present invention is high, and the success rate of parachute opening can be effectively improved.

Description

Technical Field

[0001] The present invention relates to the technical field of water rockets, and in particular to a triple-redundancy parachute cabin device for parachute opening and recovery of water rockets. Background Art

[0002] A water rocket, also known as a pneumatic water jet rocket or water-propelled rocket, is a type of propulsion rocket that uses high pressure inside the rocket to rapidly eject water from a nozzle. When the pressure inside the rocket reaches a certain level, the nozzle is released, and the water rocket, driven by the mixed pressure of air and water, soars into the sky. At the highest point, a parachute deploys from the parachute mechanism inside the water rocket's capsule, carrying the rocket safely back to Earth.

[0003] The common water rocket parachute deployment mechanism consists of a hatch attached to the rocket on one side and a rocker arm driven by a servo via a rubber band or elastic cord on the other side. The parachute is typically folded and placed inside the hatch. When the servo turns four times, the rocker arm rotates, separating the rubber band attached to the rocker arm. The elastic potential energy of the rubber band pushes the parachute outward, completing the deployment. However, when deployed in mid-air using this method, water rockets often fail to deploy and eventually crash to the ground due to the rubber band failing to separate from the rocker arm or the parachute failing to leave the hatch. This can cause direct damage to the rocket and even personal injury. Summary of the Invention

[0004] The purpose of the present invention is to provide a triple redundant parachute compartment device for water rocket parachute deployment and recovery, so as to solve the problems of unstable operation and low parachute deployment success rate of existing parachute compartment devices.

[0005] To achieve the above-mentioned object, the present invention provides a triple-redundant parachute compartment device for parachute deployment and recovery of a water rocket, comprising: a parachute compartment body, a parachute compartment door mounted on the parachute compartment body and capable of opening and closing, a parachute connected to the parachute compartment door, an air pressure control switch, and a timing servo;

[0006] The parachute compartment body is provided with an ejection assembly for ejecting the parachute;

[0007] The air pressure control switch and the timing servo are simultaneously connected to the parachute door for controlling the opening and closing of the parachute door;

[0008] When the parachute door is closed, the parachute can be folded between the parachute compartment body and the parachute door;

[0009] When the parachute door is opened, the ejection assembly ejects the parachute.

[0010] According to one aspect of the present invention, the umbrella silo body includes: an umbrella silo frame, an umbrella silo shield provided on the umbrella silo frame;

[0011] The umbrella compartment shielding edge and the umbrella compartment frame are connected to each other;

[0012] The parachute door is hingedly connected to the parachute compartment frame;

[0013] The ejection assembly is connected to the umbrella compartment frame, and the ejection assembly is arranged on the front side of the umbrella compartment shielding.

[0014] According to one aspect of the present invention, the umbrella compartment shield is made of an elastic film.

[0015] According to one aspect of the present invention, the ejection assembly includes: a plurality of first elastic cords;

[0016] The plurality of first elastic ropes are arranged to cross each other, and the plurality of first elastic ropes are fixed to each other at the crossing positions; or the plurality of first elastic ropes are arranged to be parallel to each other.

[0017] According to one aspect of the present invention, the parachute door comprises: a door body, a first connecting member provided on the inner side of the door body, and a second connecting member provided on the outer side of the door body;

[0018] One end of the door body is rotatably connected to the parachute compartment frame;

[0019] One end of the first connecting member is connected adjacent to the rotating end of the door body, and the other end thereof is connected to the parachute;

[0020] One end of the second connecting member is connected adjacent to the opening and closing end of the door body, and the other end is used to connect to the air pressure control switch and the timing servo; wherein, when the door body is in a closed state, the second connecting member is in a tensioned state, used to keep the door body closed.

[0021] According to one aspect of the present invention, the second connecting member is an elastic linear telescopic member.

[0022] According to one aspect of the present invention, the air pressure control switch and the timing servo are arranged opposite to each other in a vertical direction, and a connecting rope is connected between the air pressure control switch and the timing servo;

[0023] The opposite ends of the hook-up connecting rope are detachably connected to the air pressure control switch and the timing steering gear respectively.

[0024] According to one aspect of the present invention, the air pressure control switch comprises: an air cylinder, an air pipe, a piston, a spring and a cylindrical pin;

[0025] The upper end of the gas cylinder is open, and the lower end is provided with a baffle;

[0026] One end of the air pipe is connected to the baffle, and the other end is connected to the air source;

[0027] The piston is slidably disposed in the cylinder;

[0028] The spring is located between the piston and the baffle, and opposite ends of the spring are connected to the piston and the baffle respectively;

[0029] The cylindrical pin is arranged on a side of the piston away from the spring.

[0030] According to one aspect of the present invention, the timing servo comprises: a servo base, a rocker arm rotatably connected to the servo base, and a mainspring for timing;

[0031] The mainspring is connected to the steering gear base and the rocker arm respectively.

[0032] According to one aspect of the present invention, one end of the hook-and-loop connecting rope is provided with a latch connected to the cylindrical pin, and the other end is wound and connected to the rocker arm;

[0033] The cylindrical pin is provided with a pin hole for inserting the latch pin;

[0034] A hook is provided at one end of the second connecting member away from the door body, and the second connecting member is connected to the hooking connecting rope through the hook;

[0035] The hooking connecting rope is provided with two spaced-apart limiting structures, and the hook is located between the two limiting structures, so as to limit the movement range of the hook on the hooking connecting rope.

[0036] According to one solution of the present invention, the present invention adopts a multiple switch structure and a multiple ejection structure, so that the separation fault tolerance rate of the parachute opening process is high and the parachute opening success rate is greatly improved.

[0037] According to one solution of the present invention, the use of a second connector, an ejection assembly, and a bay shield ensures the parachute can successfully exit the bay body and the bay door. This method is no longer limited to the traditional separation mechanism separating near the highest point. The air pressure control switch and timing servo can be used to successfully deploy the parachute under any conditions. This allows for more precise control of the separation conditions and timing based on mission requirements, broadening its applicability and diversifying its use scenarios.

[0038] According to one solution of the present invention, the use of the air pressure control device and the timing servo can respectively record the flexible adjustment of the parachute opening timing of the water rocket, which greatly improves the redundancy of the parachute opening control of the present invention and effectively improves the parachute opening effect of the present invention.

[0039] According to one solution of the present invention, the structure of the present invention is simple and easy to assemble and disassemble. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 is a front view of a triple-redundant parachute cabin device according to one embodiment of the present invention;

[0041] Figure 2 is a structural diagram of a parachute door closing according to an embodiment of the present invention;

[0042] Figure 3 is a structural diagram of an air pressure control switch according to an embodiment of the present invention;

[0043] Figure 4 is an internal structural diagram of a triple-redundant parachute cabin device according to an embodiment of the present invention;

[0044] Figure 5 is a diagram of a parachute ejection structure of a triple-redundant parachute cabin device according to an embodiment of the present invention;

[0045] Figure 6 It is a diagram of the parachute deployment structure of a triple redundant parachute cabin device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0046] To more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be derived from these drawings without inventive effort.

[0047] When describing the embodiments of the present invention, the orientation or positional relationship expressed by the terms "longitudinal", "transverse", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the orientation or positional relationship shown in the relevant drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, the above terms should not be understood as limiting the present invention.

[0048] Combine Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 and Figure 6As shown, according to one embodiment of the present invention, a triple-redundant parachute chamber device for water rocket parachute deployment and recovery comprises: a parachute chamber body 1, a parachute chamber door 2 mounted on the parachute chamber body 1 and capable of opening and closing, a parachute 3 connected to the parachute chamber door 2, an air pressure control switch 4, and a timing servo 5. In this embodiment, the parachute chamber body 1 is equipped with an ejection assembly 1a for ejecting the parachute 3. The air pressure control switch 4 and the timing servo 5 are both connected to the parachute chamber door 2 to control the opening and closing of the parachute chamber door 2. In this embodiment, when the parachute chamber door 2 is closed, the parachute 3 can be folded and stored between the parachute chamber body 1 and the parachute chamber door 2. The parachute 3 can be stored in a Z-shaped folding arrangement between the parachute chamber body 1 and the parachute chamber door 2. In this embodiment, to ensure the effective ejection of the parachute 3, the parachute 3 exerts pressure on the ejection assembly 1a under the pressure of the parachute chamber door 2. Consequently, when the parachute chamber door 2 opens, the parachute 3 is effectively ejected.

[0049] Combine Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 and Figure 6 As shown, according to one embodiment of the present invention, the parachute magazine body 1 includes: a parachute magazine frame 11, and a parachute magazine shield 12 arranged on the parachute magazine frame 11. In this embodiment, the parachute magazine frame 11 is a rectangular frame as a whole, which is made of hard material, and can be conveniently embedded in the rocket body of the water rocket, facilitating a stable connection with the rocket body. In this embodiment, the edge of the parachute magazine shield 12 is interconnected with the parachute magazine frame 11; the parachute door 2 is hingedly connected to the parachute magazine frame 11. In this embodiment, the ejection assembly 1a is connected to the parachute magazine frame 11, and the ejection assembly 1a is arranged on the front side of the parachute magazine shield 12. Among them, the parachute magazine shield 12 is used to form a space for accommodating the parachute 3.

[0050] Combine Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 and Figure 6As shown, according to one embodiment of the present invention, the bay shield 12 is made of an elastic film. In this embodiment, since the bay frame 11 is generally rectangular, the shape of the bay shield 12 matches the shape of the bay frame 11 to ensure a stable connection between the edge of the bay shield 12 and the bay frame 11, thereby forming a closed storage chamber. In this embodiment, when the parachute 3 is not contained, the bay shield 12 is in a relaxed state. At this time, the storage space formed by the bay shield 12 is smaller than the volume of the entire folded parachute 3. Therefore, when the parachute 3 is placed, the parachute 3 can simultaneously tension the ejection assembly 1a and the bay shield 12. When the parachute 3 is released, the ejection assembly 1a and the bay shield 12 provide dual elastic force to eject the parachute 3, further effectively ensuring the ejection of the parachute 3. In this embodiment, the better the elasticity of the bay shield 12, the stronger the ejection force it can provide. At the same time, the size of the bay shield 12 can be controlled to adjust the size of the elastic force (for example, when the entire area of the bay shield 12 in the relaxed state can be set to be consistent with the opening of the bay frame 11, and then the accommodating space for the parachute 3 is zero at this time, after the parachute 3 is placed, the bay shield 12 can be placed in a maximum tensioned state to provide a stronger elastic force. Of course, the area of the bay shield 12 can be further reduced so that when it is connected to the bay frame 11, it has a certain initial elastic force, and then after the parachute 3 is placed, the bay shield 12 can be placed in a maximum tensioned state and provide a stronger elastic force).

[0051] like Figure 5 As shown, according to one embodiment of the present invention, the ejection assembly 1a includes: a plurality of first elastic cords 1a1. In this embodiment, the plurality of first elastic cords 1a1 are arranged in a cross-sectional arrangement and fixed to each other at the intersection. For example, two first elastic cords 1a1 are provided, each connected to a diagonal portion of the parachute frame 11 to achieve a cross-sectional arrangement, and the cross-sectional arrangement is fixed (for example, by tying a knot or securing with a connector). In this embodiment, the first elastic cords 1a1 are in a tensioned state (i.e., possessing a certain initial elastic force). This arrangement effectively ensures the effective ejection of the parachute 3. Of course, in another embodiment, the plurality of first elastic cords 1a1 are arranged parallel to each other. The first elastic cords 1a1 may be arranged parallel to the side of the parachute frame 11 and spaced apart, or the first elastic cords 1a1 may be arranged obliquely and intersecting the side of the parachute frame 11 and spaced apart. When the plurality of first elastic cords 1a1 are arranged in parallel, the spacing between adjacent first elastic cords 1a1 must be controlled within a predetermined range to ensure adequate support for the parachute 3.

[0052] Combine Figure 1 、 Figure 4 、 Figure 5 and Figure 6 As shown, according to one embodiment of the present invention, the parachute door 2 comprises a door body 21, a first connector 22 disposed on the inner side of the door body 21, and a second connector 23 disposed on the outer side of the door body 21. In this embodiment, one end of the door body 21 is a pivoting end rotatably connected to the parachute compartment frame 11, and the other end is an opening and closing end. In this embodiment, the first connector 22 is connected to the parachute 3. The first connector 22 can be made of nylon rope, with one end connected adjacent to the pivoting end of the door body 21 and the other end connected to the parachute 3. This connection method for the parachute 3 further effectively ensures that when the parachute door 2 is opened, a portion of the parachute 3 can be drawn out through the first connector 22 connected to the parachute door 2. This ensures that the force bearing point between the parachute 3 and the parachute compartment device is outside the parachute compartment body 1, further ensuring smooth deployment of the parachute 3 after ejection. In this embodiment, one end of the second connector 23 is connected adjacent to the opening and closing end of the door body 21, while the other end is connected to the air pressure control switch 4 and the timing servo 5. In this embodiment, when the second connector 23 is connected to the air pressure control switch 4 and the timing servo 5, the door body 21 can be pressed against the bay frame 11 by the second connector 23, thereby sequentially applying pressure to the parachute 3, the ejection assembly 1a, and the bay shield 12, thereby closing the door body 21. In this embodiment, the second connector 23 is in a tensioned state.

[0053] In this embodiment, the hatch body 21 can be set as a plate-like structure with an arc, and the arc is adapted to the surface arc of the installed water rocket, so that the surface of the water rocket maintains a unified structure.

[0054] Combine Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 and Figure 6 As shown, according to one embodiment of the present invention, the second connecting member 23 is an elastic linear expansion member. For example, the second connecting member 23 can be made of an elastic rope, one end of which is connected to the door body 21, and the other end is used to connect to the air pressure control switch 4 and the timing servo 5.

[0055] By adopting an elastic second connecting member 23, it can be better tensioned when closing the hatch body 21, and then when the air pressure control switch 4 or the timing servo 5 is actuated to loosen the second connecting member 23, the second connecting member 23 can be quickly retracted under the action of the elastic force, which is beneficial to ensuring the effective opening of the hatch body 21.

[0056] Combine Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 and Figure 6 As shown, according to one embodiment of the present invention, the air pressure control switch 4 and the timing servo 5 are arranged relative to each other with a spacing in the vertical direction, and a hanging connecting rope 6 is connected between the air pressure control switch 4 and the timing servo 5. In this embodiment, the opposite ends of the hanging connecting rope 6 are detachably connected to the air pressure control switch 4 and the timing servo 5 respectively. In this embodiment, the timing servo 5 is located directly above the air pressure control switch 4, and thus, the hanging connecting rope 6 can be vertically installed between the air pressure control switch 4 and the timing servo 5. The hatch body 21 can then be closed by connecting the second connecting member 23 to the hanging connecting rope 6. In this embodiment, there is a spacing between the hanging connecting rope 6 and the edge of the hatch body 21, which further facilitates the connection of the second connecting member 23 and avoids affecting the hatch body 21.

[0057] In this embodiment, the hook-and-loop connecting rope 6 can be made of a rope without elasticity, such as a nylon rope.

[0058] Combine Figure 2 and Figure 3 As shown, according to one embodiment of the present invention, the air pressure control switch 4 includes: an air cylinder 41, an air pipe 42, a piston 43, a spring 44 and a cylindrical pin 45. In this embodiment, the upper end of the air cylinder 41 is open, and a baffle is provided at the lower end. In this embodiment, one end of the air pipe 42 is connected to the baffle, and the other end is connected to the gas source; the high-pressure gas in the gas source can be transported into the air cylinder 41 through the air pipe 42. In this embodiment, the piston 43 is slidably arranged in the air cylinder 41; the spring 44 is located between the piston 43 and the baffle, and the opposite ends of the spring 44 are respectively connected to the piston 43 and the baffle. In this embodiment, the cylindrical pin 45 is arranged on the side of the piston 43 away from the spring 44, and the cylindrical pin 45 is coaxially arranged with the piston 43; wherein, the movement of the piston 43 along the air cylinder 41 can drive the corresponding movement of the cylindrical pin 45.

[0059] In this embodiment, the air source connected to air pipe 42 is the water rocket's power source. It generates power by ejecting stored water through high-pressure gas. Furthermore, when air pipe 42 delivers high-pressure gas from the air source into cylinder 41, piston 43 is lifted and spring 44 is tensioned. As the water rocket rises, the internal air pressure decreases, causing piston 43 to be gradually pulled back by spring 44, thereby disengaging from the attachment rope 6 and facilitating the opening of the parachute door 2.

[0060] Combine Figure 1 、 Figure 2 、 Figure 4 、 Figure 5 and Figure 6As shown, according to one embodiment of the present invention, the timing servo 5 comprises a servo base 51, a rocker arm 52 rotatably connected to the servo base 51, and a timing spring. In this embodiment, the spring is connected to the servo base 51 and the rocker arm 52, respectively. Rotating the rocker arm 52 twists the spring, thereby achieving mechanical timing. With this arrangement, the connecting rope 6 can be wrapped around the rocker arm 52. When the timing is complete, the connecting rope 6 can be directly detached from the rocker arm 52, thereby facilitating the timing of the opening of the parachute door 2.

[0061] Combine Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 and Figure 6 As shown, according to one embodiment of the present invention, one end of the hook-up connecting rope 6 is provided with a plug 61 connected to the cylindrical pin 45, and the other end is wound and connected with the rocker arm 52. In this embodiment, a pin hole for inserting the plug 61 is provided on the cylindrical pin 45, and the pin hole can be arranged along the radial direction of the cylindrical pin 45. In this embodiment, a loop can be provided at one end of the hook-up connecting rope 6 wound around the rocker arm 52, and the loop is sleeved on the rocker arm 52 and then wound around to achieve its winding connection function. It should be noted that in order to ensure that the loop can be smoothly removed from the rocker arm 52, the rocker arm 52 can be rotated in advance so that after the wound hook-up connecting rope 6 is released, the loop can be further detached from the rocker arm 52 by rotating the rocker arm 52.

[0062] In this embodiment, a hook is provided at the end of the second connecting member 23 away from the door body 21, and the second connecting member 23 is connected to the hooking cord 6 via the hook. In this embodiment, the hooking cord 6 is provided with two spaced-apart limiting structures, with the hook positioned between the two limiting structures to limit the range of movement of the hook on the hooking cord 6. In this embodiment, the limiting structure can be implemented as a sleeve clamped onto the hooking cord 6, or by directly tying a knot on the hooking cord 6.

[0063] With the above arrangement, since the hook-up cord 6 is detachably mounted from both the air pressure control switch 4 and the timing servo 5, detaching either end of the hook-up cord 6 from the aforementioned mechanism will disengage the second connector 23, facilitating the opening of the parachute door 2 and achieving a dual-opening effect for the parachute door 2. Furthermore, by properly adjusting the timing of the timing servo 5, the timing between the timing servo 5 and the air pressure control switch 4 can be achieved, enabling the present invention to flexibly and reliably open the parachute door 2. Furthermore, by adjusting the elastic force, material, and length of the spring 44 in the air pressure control switch 4, the timing of the opening of the parachute door 2 can be controlled, further enhancing the flexibility of the present invention.

[0064] According to one embodiment of the present invention, the pinhole in cylindrical pin 45 has a circular cross-section. In this embodiment, the pinhole is a circular through-hole with a constant cross-sectional diameter. Alternatively, the pinhole can be configured as a circular through-hole with a variable cross-sectional diameter (for example, with a larger diameter at each end and a smaller diameter in the middle, forming a hole with a smaller opening in the middle and larger openings at both ends). This configuration of the pinhole allows the connecting rope 6 to gradually move upward relative to the piston as it moves downward, causing the latch 61 to deform due to the increasing torque applied, ultimately freeing the connecting rope from the opening. In particular, configuring the pinhole as a through-hole with a variable radial diameter facilitates the removal of the latch 61, reduces resistance to removal, and ensures reliable and stable latch removal according to the present invention.

[0065] According to the present invention, the triple protection of the elastic potential energy of the cross-elastic cords, the air pressure control switch, and the timing servo ensures the successful release of the parachute from the parachute compartment and deployment. During deployment, the parachute, pressed against the cross-elastic cords, is ejected from the parachute compartment by the elastic cords. Furthermore, the air pressure control switch and the timing servo provide dual assurance that the elastic cords used to close the parachute compartment door will be released, thereby ensuring the successful release of the parachute from the compartment, effectively achieving a triple-redundant deployment effect.

[0066] To further illustrate the present invention, its operation process is further described.

[0067] S1, tie the parachute 3 rope to the first connecting member 22 connected to the hatch body 21, and fold the parachute 3 in a Z-shape according to the size of the parachute compartment frame 11 and place it on the ejection assembly 1a;

[0068] S2, wind the end of the connecting rope 6 without the pin 61 around the rocker arm 52 of the timing servo 5, and set the number of spring rotations according to the parachute opening timing required for launch;

[0069] S3, insert the latch 61 of the hooking connecting rope 6 into the pin hole of the cylindrical pin 45;

[0070] S4, closing the hatch body 21, thereby pressing the parachute 3, the ejection assembly 1a, and the parachute compartment shield 12 into the water rocket, and ensuring that the parachute 3 is not entangled with the parachute compartment body 1 and the water rocket;

[0071] S5, stretching the second connecting member 23 and hanging the hook provided at its end on the hanging connecting rope 6;

[0072] S6, after the rocket is launched, when the separation condition is met, the hook at the end of the second connecting member 23 is released from the attachment rope 6, and the second connecting member 23 is ejected due to its elastic potential energy. Combined with the rebound force of the ejection assembly 1a and the parachute shield 12, the hatch body 21 is quickly ejected. The separation condition is: the timing of the timing servo 5 has expired, the rocker arm 52 is separated from the attachment rope 6, and / or the internal pressure of the water rocket decreases, and the latch 61 is disengaged from the pin hole of the cylindrical pin 45 under the tension of the spring 44.

[0073] S7, since the door body 21 is opened first, the door body 21 can pull the first connecting member 22 apart, and a gap is generated between the parachute 3 and the door body 21;

[0074] S8, further, the compressed ejection assembly 1a and the parachute compartment shield 12 further eject the Z-shaped folded parachute 7 due to elastic potential energy, completing the parachute opening.

[0075] According to the present invention, the parachute cabin device in this solution realizes convenient and quick connection and separation operations, the parachute opening process is stable and reliable, and the multiple redundancy parachute opening fully ensures the success rate of the parachute 3.

[0076] Furthermore, by using the air pressure control switch 4 and the timing servo 5, the opening time of the parachute 3 can be flexibly adjusted, and double protection is also provided to ensure the successful release of the hanging connecting rope 6.

[0077] Furthermore, the use of the second connector 23, ejection assembly 1a, and bay shield 12 ensures that the parachute 3 can successfully leave the bay body 1 and bay door 2. This method is no longer limited to the traditional separation device separation condition near the highest point. The air pressure control switch 4 and timer servo 5 can be used to successfully open the parachute 3 under any conditions. The separation conditions and time can be more effectively set according to mission requirements, thus expanding the scope of application and diversifying usage scenarios.

[0078] The above contents are merely examples of specific solutions of the present invention. For devices and structures not described in detail, it should be understood that they can be implemented by adopting general devices and methods available in the art.

[0079] The above description is merely one embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that the present invention is susceptible to various modifications and variations. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. A triple-redundant parachute cabin device for water rocket parachute recovery, characterized in that: include: A parachute compartment body (1), a parachute compartment door (2) mounted on the parachute compartment body (1) and capable of opening and closing, a parachute (3) connected to the parachute compartment door (2), an air pressure control switch (4), and a timing servo (5); The parachute compartment body (1) is provided with an ejection assembly (1a) for ejecting the parachute (3); The air pressure control switch (4) and the timing servo (5) are simultaneously connected to the parachute door (2) and are used to control the opening and closing of the parachute door (2); When the parachute door (2) is closed, the parachute (3) is foldable and located between the parachute compartment body (1) and the parachute door (2); When the parachute door (2) is opened, the ejection assembly (1a) ejects the parachute (3); The parachute door (2) comprises: a door body (21), and a second connecting member (23) arranged outside the door body (21); The air pressure control switch (4) and the timing steering gear (5) are arranged relative to each other in a vertical direction, and a connecting rope (6) is connected between the air pressure control switch (4) and the timing steering gear (5); The opposite ends of the hook-and-loop connecting rope (6) are detachably connected to the air pressure control switch (4) and the timing servo (5). The air pressure control switch (4) comprises: an air cylinder (41), an air pipe (42), a piston (43), a spring (44) and a cylindrical pin (45); The upper end of the gas cylinder (41) is open, and the lower end is provided with a baffle; One end of the air pipe (42) is connected to the baffle, and the other end is connected to the air source; The piston (43) is slidably disposed in the gas cylinder (41); The spring (44) is located between the piston (43) and the baffle, and opposite ends of the spring (44) are connected to the piston (43) and the baffle respectively; The cylindrical pin (45) is arranged on a side of the piston (43) away from the spring (44); One end of the hooking connecting rope (6) is provided with a latch pin (61) connected to the cylindrical pin (45); The cylindrical pin (45) is provided with a pin hole for inserting the latch pin (61); A hook is provided at one end of the second connecting member (23) away from the hatch body (21), and the second connecting member (23) is connected to the hook connection rope (6) via the hook.

2. The triple-redundant parachute cabin device according to claim 1, characterized in that: The umbrella bin body (1) comprises: an umbrella bin frame (11), and an umbrella bin shield (12) provided on the umbrella bin frame (11); The edge of the umbrella compartment shield (12) is connected to the umbrella compartment frame (11); The parachute door (2) is hingedly connected to the parachute compartment frame (11); The ejection assembly (1a) is connected to the umbrella compartment frame (11), and the ejection assembly (1a) is arranged on the front side of the umbrella compartment shield (12).

3. The triple-redundant parachute cabin device according to claim 2, characterized in that: The umbrella compartment shield (12) is made of an elastic film.

4. The triple-redundant parachute cabin device according to claim 3, characterized in that: The ejection assembly (1a) comprises: a plurality of first elastic ropes (1a1); The plurality of first elastic ropes (1a1) are arranged to cross each other, and the plurality of first elastic ropes (1a1) are fixed to each other at the crossing positions; or the plurality of first elastic ropes (1a1) are arranged to be parallel to each other.

5. The triple-redundant parachute cabin device according to claim 4, characterized in that: The parachute door (2) further comprises: a first connecting member (22) provided on the inner side of the door body (21); One end of the door body (21) is rotatably connected to the parachute compartment frame (11); One end of the first connecting member (22) is connected adjacent to the rotating end of the door body (21), and the other end is connected to the parachute (3); One end of the second connecting member (23) is connected adjacent to the opening and closing end of the door body (21), and the other end is used to connect to the air pressure control switch (4) and the timing servo (5); wherein, when the door body (21) is in a closed state, the second connecting member (23) is in a tensioned state, and is used to keep the door body (21) closed.

6. The triple-redundant parachute cabin device according to claim 5, characterized in that: The second connecting member (23) is an elastic linear telescopic member.

7. The triple-redundant parachute cabin device according to claim 6, characterized in that: The timing servo (5) comprises: a servo base (51), a rocker arm (52) rotatably connected to the servo base (51), and a clockwork spring for timing; The mainspring is connected to the steering gear base (51) and the rocker arm (52) respectively.

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