Multi-rocket co-driven low-altitude quick parachute opening device and low-altitude aircraft
Patent Information
- Application Number
- CN202511327728.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-17
- Publication Date
- 2026-01-09
AI Technical Summary
Existing single-rocket parachute launch devices have insufficient parachute pull-out acceleration when the load exceeds 50kg, which cannot overcome the initial resistance of the folded canopy, resulting in delayed parachute opening. Furthermore, increasing the rocket thrust would make the device too large and heavy, affecting the normal flight of low-altitude aircraft.
The system employs a multi-rocket coordinated low-airspeed parachute deployment device, which achieves rapid and stable parachute deployment through the coordinated operation of multiple synchronously launched parachute rockets. The total thrust is evenly distributed among the four rockets, reducing the thrust requirement of each individual rocket. The system also utilizes a modular design and rope assembly to ensure the synchronicity and reliability of the parachute deployment process.
It achieved stable deployment of the parachute under extreme conditions, reduced the size and mass of the rocket, and ensured the safe landing of low-altitude aircraft.
Smart Images
Figure CN121291775A_ABST
Abstract
Description
Technical Field
[0001] This disclosure relates to the fields of aerospace low-altitude recovery and emergency parachute deployment technology, specifically to a multi-arrow coordinated low-altitude parachute deployment device and a low-altitude aircraft. Background Technology
[0002] Against the backdrop of the rapid rise of the global low-altitude economy, low-altitude airspace is experiencing explosive growth as a new strategic resource. The commercialization of scenarios such as urban air mobility (UAM), drone logistics, low-altitude tourism, and emergency rescue is accelerating. This industrial wave poses systemic challenges to low-altitude safety technologies, among which the performance of the low-altitude rapid parachute deployment device, as a core safety redundancy system, directly restricts the sustainable development of the low-altitude economy. Summary of the Invention
[0003] This disclosure provides a multi-arrow coordinated low-airspeed parachute opening device, comprising:
[0004] The parachute compartment is configured to accommodate stacked parachutes.
[0005] Multiple launch bays are evenly distributed around the outer wall of the parachute compartment, and each launch bay is configured to house a parachute rocket.
[0006] Multiple connecting compartments are respectively connected to the outer side wall of the parachute pack compartment, and each connecting compartment is configured to house part of a rope assembly that connects the parachute rocket and the parachute pack.
[0007] In some embodiments, the angle between the axis of each launch compartment and the axis of the parachute compartment is 5° to 10°.
[0008] In some embodiments, the parachute compartment has a cross-section perpendicular to its axis that is a regular polygon, and the number of launch compartments is equal to the number of sides of the regular polygon.
[0009] In some embodiments, the multi-arrow coordinated low-airspeed parachute deployment device further includes:
[0010] Parachute rocket, configured to be housed in the launch chamber, the parachute rocket comprising:
[0011] Rocket body;
[0012] The ignition head and the flame nozzle are respectively located at both ends of the rocket body;
[0013] Multiple rope connectors are evenly arranged around the outer wall of the rocket body and located on the outer wall of the rocket body near the flame nozzle area.
[0014] In some embodiments, each launch chamber includes:
[0015] Launch chamber body;
[0016] A launch bay sealing cover, fastened to the launch bay body, to protect the parachute rocket housed within the launch bay body, the launch bay sealing cover comprising:
[0017] Cover;
[0018] A limiting hole is provided on the side of the cover facing the parachute rocket, configured to accommodate and limit the ignition head;
[0019] Multiple limiting plates are evenly distributed along the circumference of the cover and extend from the edge of the cover toward the parachute rocket, configured to contact the sidewall of the rocket body of the parachute rocket to limit the rocket body.
[0020] In some embodiments, the ignition head is an electric ignition head, and the electric ignition heads of the multiple parachute rockets in the multiple launch chambers are configured to synchronously receive a start-up electrical signal to launch the multiple parachute rockets synchronously.
[0021] In some embodiments, the rope assembly further includes:
[0022] Fireproof protective ring;
[0023] The first rope connects the fireproof protective ring to the rope connector;
[0024] The second rope connects the fireproof protective ring to the parachute pack; a portion of the second rope is folded and housed in the connecting compartment.
[0025] The fireproof protection ring is configured to prevent the flame ejected by the flame nozzle from directly contacting the first rope and / or the second rope, and to break when subjected to an external force greater than a threshold.
[0026] In some embodiments, the fire-resistant protective ring includes:
[0027] N first components and N second components are connected end-to-end to form a closed frame structure. The first components are connected to the rope connector via a first rope, and the second components are connected to the parachute via a second rope. Here, N is a positive integer and N≥3.
[0028] A fracture structure is provided at the connection between the first component and the second component. The fracture structure is configured to break when the external force it receives exceeds a threshold, thereby separating the first component and the second component at the connection.
[0029] In some embodiments, the umbrella compartment includes:
[0030] Parachute bag warehouse body;
[0031] The parachute compartment sealing cover is fastened to the parachute compartment body to protect the parachute housed in the parachute compartment body.
[0032] This disclosure provides some embodiments of a low-altitude aircraft, which includes the multi-arrow coordinated low-altitude parachute deployment device provided in the foregoing embodiments.
[0033] The above-described solutions in this disclosure can have the following beneficial effects:
[0034] The multi-rocket coordinated low-altitude parachute deployment device disclosed herein achieves rapid and stable parachute deployment through the coordinated operation of multiple synchronously launched parachute rockets. At the same time, the total thrust required by the deployment device is evenly distributed to the four rockets, reducing the thrust required by a single rocket, thereby reducing the size and mass of the rockets. Attached Figure Description
[0035] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this disclosure and, together with the description, serve to explain the principles of this disclosure. It is obvious that the drawings described below are merely some embodiments of this disclosure, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort. In the drawings:
[0036] Figure 1 This is a schematic diagram of the structure of a multi-arrow coordinated low-airspeed parachute opening device provided in some embodiments of this disclosure;
[0037] Figure 2 for Figure 1 The diagram shows a cross-sectional view of the multi-arrow coordinated low-airspeed parachute deployment device along line A-A'.
[0038] Figure 3 for Figure 1 An exploded view of the structure of the multi-arrow coordinated low-altitude parachute deployment device shown in the figure.
[0039] Figure 4 A schematic diagram of the structure of the parachute rocket housed in the launch chamber of the multi-rocket coordinated low-airspeed parachute opening device provided in some embodiments of this disclosure;
[0040] Figure 5 This is a schematic diagram of the structure of the launch chamber sealing cover provided in some embodiments of this disclosure;
[0041] Figure 6 A schematic diagram of a parachute rocket in launch state, provided in some embodiments of this disclosure;
[0042] Figure 7 This is a structural schematic diagram of the fireproof protective ring of a rope assembly provided in some embodiments of this disclosure. Detailed Implementation
[0043] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this invention, and not all of them. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this invention.
[0044] The terminology used in the embodiments of this invention is for the purpose of describing particular embodiments only and is not intended to limit the invention. The singular forms “a,” “the,” and “the” as used in the embodiments of this invention and the appended claims are also intended to include the plural forms, and “multiple” generally includes at least two unless the context clearly indicates otherwise.
[0045] It should be understood that the term "and / or" used in this article is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, and B existing alone. Additionally, the character " / " in this article generally indicates that the preceding and following related objects have an "or" relationship.
[0046] It should be understood that although the terms first, second, third, etc. may be used to describe the invention in the embodiments, the invention should not be limited to these terms.
[0047] It should also be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that an article or device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such an article or device. Without further limitation, an element defined by the phrase "comprising one" does not exclude the presence of other identical elements in the article or device that includes said element.
[0048] As low-altitude aircraft, such as drones, become increasingly sophisticated, their weight is also increasing. For low-altitude aircraft weighing tons, such as flying cars, the required parachutes are even larger and heavier. Existing single-rocket parachute deployment devices have limitations in thrust output; when the load exceeds 50kg, the parachute pull-out acceleration is less than 1.5G, which cannot overcome the initial drag of the folded canopy, resulting in a deployment delay rate exceeding 25%. Simply increasing the rocket thrust would make the rocket too large and heavy, affecting the normal flight of the low-altitude aircraft. To achieve both lightweight design and ensure that the parachute rocket can successfully deploy the parachute, a stable and rapid deployment device is urgently needed.
[0049] To overcome the above-mentioned defects, this disclosure provides a multi-rocket coordinated low-altitude parachute deployment device, which includes: a parachute pack compartment configured to house stacked parachutes; multiple launch compartments evenly distributed around the outer wall of the parachute pack compartment, each launch compartment being configured to house a parachute rocket; and multiple connecting compartments respectively connecting the multiple launch compartments to the outer wall of the parachute pack compartment, each connecting compartment being configured to house part of a rope assembly, the rope assembly connecting the parachute rocket and the parachute pack.
[0050] The multi-rocket coordinated low-altitude parachute deployment device disclosed herein achieves rapid and stable parachute deployment through the coordinated operation of multiple synchronously launched parachute rockets. At the same time, the total thrust required by the deployment device is evenly distributed to the four rockets, reducing the thrust required by a single rocket, thereby reducing the size and mass of the rockets.
[0051] The optional embodiments of the present invention will now be described in detail with reference to the accompanying drawings.
[0052] Figure 1 This is a schematic diagram of the structure of a multi-arrow coordinated low-airspeed parachute deployment device provided in some embodiments of this disclosure. Figure 2 for Figure 1 The diagram shows a cross-sectional view of the multi-arrow coordinated low-airspeed parachute deployment device along line A-A'. Figure 3 for Figure 1 The diagram shown is an exploded view of the structure of the multi-arrow coordinated low-altitude parachute deployment device.
[0053] like Figures 1 to 3 As shown, some embodiments of this disclosure provide a multi-rocket coordinated low-altitude parachute opening device 100, which includes a parachute pack compartment 10, a launch compartment 20, and a connecting compartment 30.
[0054] The parachute compartment 10 has a accommodating space configured to accommodate stacked parachutes 40. There are multiple launch compartments 20, for example, three or more, which are evenly distributed around the outer side wall of the parachute compartment 10, and each launch compartment 20 is configured to accommodate one parachute rocket 50.
[0055] Multiple connecting compartments 30, each corresponding to a launch compartment 20, are respectively connected to the outer side wall of the parachute pack compartment 10. Each connecting compartment 30 is configured to house part of a rope assembly 60, which connects the parachute rocket 50 and the parachute pack 40.
[0056] In this embodiment, multiple launch chambers carrying parachute rockets are evenly distributed on the outer sidewall of the parachute pack chamber. Each launch chamber's parachute rocket is precisely connected to a dedicated connection point on the top of the parachute pack via an independent rope assembly. When the multi-rocket coordinated low-airspeed parachute deployment device receives the deployment command, multiple parachute rockets simultaneously trigger the ignition mechanism, generating coordinated thrust within milliseconds to quickly overcome aerodynamic drag in low-airspeed environments. The rope traction system enables instantaneous release and rapid inflation of the parachute canopy, ensuring a stable deployment posture of the parachute under extreme conditions.
[0057] In some embodiments, such as Figure 2 As shown, the angle between the axis AX2 of each launch chamber 20 and the axis AX1 of the parachute compartment 10 is 5° to 10°. That is, multiple launch chambers 20 are arranged to extend outwards at an angle of 5° to 10°, specifically, for example, 7°. This arrangement ensures that the multi-directional thrust vectors generated when multiple parachute rockets 50 are launched synchronously do not interfere with each other, and also avoids interference and entanglement risks of high-temperature exhaust flow on the rope assembly 60 through a pre-set rope assembly release trajectory guidance mechanism, thereby ensuring the synchronicity of the parachute opening action and the reliability of the deployment process.
[0058] In some embodiments, such as Figure 3 As shown, the cross-section of the parachute compartment 10 perpendicular to its axis AX1 is a regular polygon, and the number of launch compartments 20 is equal to the number of sides of the regular polygon. Specifically, the cross-section of the parachute compartment 10 perpendicular to its axis AX1 is, for example, a square, and the number of launch compartments 20 is, for example, four, with each launch compartment 20 located at the middle of the outer wall of its corresponding parachute compartment 10.
[0059] In other embodiments, the parachute compartment 10 has a cross-section perpendicular to its axis AX1, for example, that is a regular hexagon, and the number of launch compartments 20 is, for example, 6.
[0060] In some embodiments, each launch chamber 20 corresponds to a vertex of the regular polygon, and the launch chamber is located at the outer edge of its corresponding parachute chamber 10.
[0061] In some embodiments, the parachute compartment 10 has a circular cross-section perpendicular to its axis AX1, and a plurality of launch compartments 20 are evenly arranged on the outer peripheral wall of the parachute compartment 10.
[0062] In some embodiments, the multi-rocket-assisted low-altitude parachute deployment device 100 adopts a single modular parachute pack structure, internally integrating a folded ring-sail canopy system. This canopy system is securely connected to the target carrier, such as a low-altitude aircraft, via a dedicated connection interface using high-strength parachute lines. Multiple sets of connectors are evenly arranged circumferentially on the top of the parachute pack 40, each connected to multiple rope assemblies 60. The multiple telescopic assemblies 60 are arranged radially. Initially, they are pre-tensioned with the parachute pack 40 via a tension adjustment mechanism. When the deployment command is triggered, the rope assemblies 60 unfold along a preset release trajectory under the action of the parachute rockets, ensuring rapid inflation and deployment of the canopy without tangling or interference at low airspeed conditions. Simultaneously, the tension transmission mechanism of the parachute lines achieves stable deceleration control of the target carrier.
[0063] Figure 4 This is a schematic diagram of the structure of the parachute rocket housed in the launch chamber of the multi-rocket coordinated low-airspeed parachute deployment device provided in some embodiments of this disclosure, combined with... Figures 1 to 4 As shown, the multi-rocket coordinated low-altitude parachute deployment device 100 also includes a parachute rocket 50, which is configured to be installed in the launch chamber 20. The parachute rocket 50 includes: a rocket body 51, an ignition head 52, a flame nozzle 53, and multiple rope connectors.
[0064] The rocket body 51 has a generally cylindrical structure. The ignition head 52 and the flame nozzle 53 are respectively located at both ends of the rocket body 51. Upon receiving an ignition command, the ignition head 52 will activate the parachute rocket 50 within milliseconds. The flame nozzle 53 ejects a high-temperature flame, and the resulting high-temperature exhaust flow propels the parachute rocket 50 rapidly out of the launch chamber 20 along its axis AX2. Multiple rope connectors 54, for example, four, are evenly arranged around the outer wall of the rocket body 51, located near the flame nozzle area 53. Figure 3 and Figure 4 As shown, the end of the rocket body 51 of the parachute rocket 50 near the ignition head 52 has a gradually tapering arc surface, which helps to reduce the air resistance of the parachute rocket.
[0065] Figure 5 This is a schematic diagram of the structure of the launch chamber sealing cover provided in some embodiments of this disclosure. (In conjunction with...) Figures 3 to 4 As shown, each launch chamber 20 includes a launch chamber body 21 and a launch chamber sealing cover 22.
[0066] The launch chamber sealing cover 22 is fastened to the launch chamber body 21 to protect the parachute rocket 50 housed in the launch chamber body 21. The launch chamber sealing cover 22 includes a cover body 221, a limiting hole 222, and a limiting plate 223. The cover body 221 has a plate-like structure, and the limiting hole 222 is located on the side of the cover body 221 facing the parachute rocket 50. It is configured to house and limit the ignition head 52 of the parachute rocket 50, protecting the ignition head 52 and preventing it from moving erratically.
[0067] Multiple limiting plates 223 are evenly distributed circumferentially along the cover 221 and extend from the edge of the cover 221 toward the parachute rocket 50. They are configured to contact the sidewall of the rocket body 51 of the parachute rocket to limit the rocket body 51 and prevent it from swaying within the launch chamber 21. For example, there are four limiting plates 223, and the accommodating space enclosed by these limiting plates 223 at least accommodates the arcuate end of the rocket body 51 near the ignition head 52.
[0068] In some embodiments, the ignition head 52 of the parachute rocket 50 is an electric ignition head, and the electric ignition heads of the multiple parachute rockets 50 in the multiple launch chambers 20 are configured to synchronously receive the start-up electrical signal, enabling the multiple parachute rockets 50 to be launched synchronously at millisecond-level synchronization. The parachute rocket 50 adopts a modular design, with its internal core component being a high-performance composite solid propellant unit. Its combustion chamber is optimized to form a central ignition type multi-point simultaneous ignition mechanism. When a start-up command is received, the propellant rapidly combusts to generate high-temperature, high-pressure gas, which efficiently converts thermal energy into axial thrust through a convergent-divergent nozzle, propelling the parachute rocket to achieve instantaneous acceleration along a preset launch trajectory.
[0069] Specifically, when the drone triggers the parachute deployment mechanism, electrical signals are simultaneously transmitted to the electric ignition heads of multiple parachute rockets 50. The electric ignition heads respond instantaneously and ignite the propulsion system 5, causing multiple parachute rockets to launch synchronously and instantly. At the same time, the rope assembly pulls the traction point at the top of the main canopy of the parachute pack, causing the main canopy to initially detach from the parachute pack 40, forming a "canopy prototype." After the main canopy detaches, high-speed airflow rushes into the canopy through the air inlets at the edge of the canopy, using air pressure to cause the canopy to expand rapidly radially, achieving parachute deployment. The four rockets trigger the ignition mechanism simultaneously, generating synergistic thrust within milliseconds, quickly overcoming aerodynamic drag in low-airspeed environments. The rope traction system enables instantaneous release and rapid inflation of the canopy, ensuring the parachute achieves a stable deployment attitude under extreme conditions.
[0070] Figure 6 This is a schematic diagram of the structure of a parachute rocket in the launch state provided in some embodiments of this disclosure, combined with... Figure 3 and Figure 6 As shown, the rope assembly 60 also includes a fireproof protective ring 61, a first rope 62, and a second rope 63.
[0071] The first rope 61 connects the fireproof protective ring 61 to the rope connector 54 of the parachute rocket 50; the second rope 63 connects the fireproof protective ring 61 to the parachute pack 40, with a portion of the second rope 63 folded and housed in the connecting compartment 30. The fireproof protective ring 61 is configured to prevent the flame ejected from the flame nozzle 53 from directly contacting the first rope 62 and / or the second rope 63, and to break when subjected to an external force greater than a threshold. This ensures that during the release of the parachute pack after launch, the exhaust flame of the parachute rocket is located within the gap enclosed by the fireproof protective ring, preventing the ropes from burning through, and ensuring timely separation of the deployed parachute from the parachute rocket, achieving a rapid parachute deployment.
[0072] Figure 7 This is a schematic diagram of the structure of the fireproof protective ring of the rope assembly provided in some embodiments of this disclosure, such as... Figure 7 As shown, the fire protection ring 61 includes multiple first components 611 and multiple second components 612.
[0073] The number of first components 611 and second components 612 is, for example, N, where N is a positive integer and N≥3. N first components 611 and N second components 612 are alternately connected end-to-end to form a closed frame structure. The first components 611 are configured to be connected to the parachute rocket 50 via a first rope 62, and the second components 612 are configured to be connected to the parachute pack 40 via a second rope 63. After launch, multiple parachute rockets 50 work together to pull the parachute pack 40, enabling rapid inflation and release of the parachute. The rocket thrust pulls the parachute pack 40 to a safe distance, ensuring the parachute fully deploys before the aircraft lands, providing cushioning protection. During the release of the parachute pack after launch, the exhaust flame of the parachute rocket 50 is located within the gap enclosed by the closed frame, preventing the ropes from burning and ensuring the effectiveness of the parachute deployment.
[0074] A fracture structure 613 is provided at the connection between the first component 611 and the second component 612. This fracture structure is configured to break when the applied external force exceeds a threshold, causing the first component 611 and the second component 612 to separate at the connection. After the parachute rocket 50 completes its release from the parachute pack 40, it must detach from the parachute as quickly as possible. If separation is not achieved in time, the high-speed movement of the rocket shell may impact the fully deployed parachute surface, leading to structural damage or disrupting the parachute's aerodynamic balance, thereby affecting the overall system's safety and stability.
[0075] In this embodiment, the parachute rocket 50 and the parachute pack 40 are connected by ropes through the fireproof protection ring 61. The structure is simple and highly reliable, ensuring timely separation of the parachute rocket 50 and the parachute pack 40 while avoiding damage to the parachute pack.
[0076] Combination Figures 3 to 7As shown, the parachute rocket 50 is connected to the parachute pack 40 via a rope assembly 60. Specifically, the parachute rocket 50 is connected to the fireproof protection ring 61 via a first rope 62, for example, to the first assembly 611 of the fireproof protection ring 61. The parachute pack 40 is connected to the fireproof protection ring 61 via a second rope 63, for example, to the second assembly 63 of the fireproof protection ring 61. The fireproof protection ring 61 is a closed frame structure that provides support. During the process of the parachute rocket 50 pulling the parachute pack 40, due to the supporting effect of the fireproof protection ring 61, the first rope 62 and / or the second rope 63 will not converge towards the center after being straightened. The exhaust flame of the parachute rocket 50 is located in the gap enclosed by the closed frame structure and will not burn the first rope 62 and / or the second rope 63, ensuring that the parachute pack 40 fully deploys after being quickly released by the parachute rocket.
[0077] In some embodiments, such as Figure 7 As shown, the first component 611 and the second component 612 are both arc-shaped segments, and the closed frame structure is a closed ring. For example, there are four of each of the first component 611 and the second component 612.
[0078] In some embodiments, such as Figure 7 As shown, the fracture structure 613 is located at at least one end of the second component 612, and the fracture structure includes a weakening groove 6121. The weakening groove 6121 is a pre-fabricated notch cut at the end of the second component 612 that connects to the first component 611. The size of the weakening groove can be adjusted according to actual needs, so that the fireproof protection ring 61 breaks at the required tensile limit, thereby ensuring that the parachute rocket 50 separates from the parachute pack 40 at the correct time.
[0079] In some embodiments, the fragility structure 613 is located at one end of the second component 612, and in other embodiments, the fragility structure 613 is located at both ends of the second component 612.
[0080] After the parachute rocket 50 fully pulls out the parachute pack 40, the parachute rocket will continue to move forward due to inertia. When the parachute rocket 50 pulls the parachute pack 40 again, the fireproof protection ring 61 will be subjected to a large tensile force. Once this tensile force exceeds the pressure limit of the predetermined vulnerable part, namely the fragile structure 613, the fireproof protection ring 61 will break, that is, the connection between the first component 611 and the second component 612 will break, and the second rope 63 will slip off the second component 612 and detach from the fireproof protection ring 61, thereby separating the parachute rocket 50 and the parachute pack 40.
[0081] The fireproof protective ring 61 with an easily breakable structure is used for tensile fracture separation, replacing the explosive bolt separation method used in related technologies. The structure is simpler, the performance is more reliable, and no fragments are generated, avoiding scratches on the parachute.
[0082] In some embodiments, such as Figure 7 As shown, the first component 611 is provided with a groove 6111, configured to restrict the sliding of the first rope 62 on the first component 611. The groove 6111 essentially confines the first rope 62 within the groove 6111, ensuring that during the process of the parachute rocket 50 towing the parachute pack 40, the multiple first ropes 62 connecting the parachute rocket 50 and the fireproof protection ring 61 are evenly distributed, with each first component 611 connected to one first rope 62. This ensures uniform tension between the parachute rocket 50 and the fireproof protection ring 61, guaranteeing the stability of the parachute pack towing process.
[0083] The design of the groove 6111 also prevents the first rope connecting the first component 611 from slipping onto the second component 612 due to vibration or other reasons, thus preventing the fireproof protection ring 61 from malfunctioning.
[0084] In some embodiments, a plurality of first components 611 are evenly distributed on a closed ring, and a plurality of first ropes 62 are of the same length. During the process of the parachute rocket 50 pulling the parachute pack 40, the closed ring is substantially parallel to the bottom surface of the parachute rocket and substantially coaxial.
[0085] In some embodiments, the size of the gap enclosed by the closed frame structure is greater than or equal to the size of the bottom surface of the parachute rocket 50, specifically, as shown in... Figure 1 As shown, the diameter of the gap enclosed by the closed ring is greater than or equal to the diameter of the bottom surface of the parachute rocket, ensuring that the exhaust flame of the parachute rocket can pass through.
[0086] In some embodiments, the first component 611 and the second component 612 are both made of heat-resistant materials to prevent the fireproof protection ring 61 formed by the first component 611 and the second component 612 from deforming or being damaged due to proximity to the tail flame of the parachute, thus affecting the parachute recovery effect.
[0087] In some embodiments, such as Figure 7 As shown, the first component 611 is thicker than the second component 612. Specifically, the fragility structure 613 is located at the end of the thinner second component, making it easier to control the breakage of the fragility structure. In some embodiments, the surface of the second component 612 is designed to be smooth to ensure that the fragility structure 613 can be quickly detached from the second component 612, thereby achieving the separation of the parachute rocket 50 from the parachute pack 40.
[0088] In some embodiments, the surface of the second component 612 is designed to be smooth, allowing the second rope 63 to slide on it. After the parachute rocket 50 fully pulls out the parachute pack 40, the rocket will continue to move forward due to inertia. When the rocket pulls the parachute pack 40 again, the fireproof ring 61 will bear a large tension. The second rope 63 connected to the second component 612 may randomly slide to one end of the component, causing the fragile structure 613 at that end to bear a large force. Once the tension exceeds the predetermined pressure limit of the fragile part, the fragile structure 613, the fireproof ring 61 will break, and the second component 612 will break at that end, detaching from the first component 611 connected to that end. The second rope 63 will slip off the second component 612, thereby causing the parachute pack to detach from the fireproof ring 61 and then from the parachute rocket.
[0089] In some embodiments, the fracturing structures 613 at both ends of the same second component 612 will not break simultaneously due to differences in stress. After the fracturing structure 613 at one end of each second component 612 breaks, the second rope 63 detaches from that second component 612, and the stress on the fracturing structure 613 at the other end of the second component 612 will be below its bearing capacity, thus preventing it from breaking. That is, each second component 612 only breaks the fracturing structure 613 at one end, and the second component 612 is not completely detached from the first component 611, but is still pulled together by the parachute rocket 50. This prevents the second component 612 from detaching and scratching the parachute pack.
[0090] In some embodiments, the extension length of the first component 611 is equal to the extension length of the second component 612. For example... Figure 7 As shown, the arc lengths of the first component 611 and the second component 612 are basically the same. This design allows the first rope 62 connected to multiple first components 611 and the second rope 63 connected to multiple second components 612 to be evenly distributed during the process of the parachute rocket 50 pulling the parachute pack 40, ensuring that the fireproof protection ring 61 and the parachute pack are subjected to relatively uniform force and ensuring the stability of the parachute launching process.
[0091] like Figure 3 As shown, in some embodiments, the parachute compartment 10 includes a parachute compartment body 11 and a parachute compartment sealing cover 12. The parachute compartment sealing cover 12 is fastened to the parachute compartment body 11 to protect the parachute 40 housed in the parachute compartment body 11.
[0092] This disclosure also provides a low-altitude aircraft, which includes the multi-arrow coordinated low-altitude parachute deployment device described in the foregoing embodiments. The low-altitude aircraft may be, for example, a drone or a flying car.
[0093] Finally, it should be noted that the various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the systems or apparatus disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the descriptions are relatively simple, and relevant parts can be referred to the method section.
[0094] The above embodiments are only used to illustrate the technical solutions of this disclosure, and are not intended to limit it. Although this disclosure has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this disclosure.
Claims
1. A multi-arrow coordinated low-airspeed parachute deployment device, characterized in that, The multi-arrow coordinated low-airspeed parachute deployment device includes: The parachute compartment is configured to accommodate stacked parachutes. Multiple launch bays are evenly distributed around the outer wall of the parachute compartment, and each launch bay is configured to house a parachute rocket. Multiple connecting compartments are respectively connected to the outer side wall of the parachute pack compartment, and each connecting compartment is configured to house part of a rope assembly that connects the parachute rocket and the parachute pack.
2. The multi-arrow coordinated low-airspeed parachute deployment device according to claim 1, characterized in that, The angle between the axis of each launch compartment and the axis of the parachute compartment is 5° to 10°.
3. The multi-rocket coordinated low-airspeed parachute deployment device according to claim 1 or 2, characterized in that, The cross-section of the parachute compartment perpendicular to its axis is a regular polygon, and the number of launch compartments is equal to the number of sides of the regular polygon.
4. The multi-rocket coordinated low-airspeed parachute deployment device according to claim 1 or 2, characterized in that, The multi-arrow coordinated low-airspeed parachute deployment device also includes: Parachute rocket, configured to be housed in the launch chamber, the parachute rocket comprising: Rocket body; The ignition head and the flame nozzle are respectively located at both ends of the rocket body; Multiple rope connectors are evenly arranged around the outer wall of the rocket body and located on the outer wall of the rocket body near the flame nozzle area.
5. The multi-arrow coordinated low-airspeed parachute deployment device according to claim 4, characterized in that, Each launch chamber includes: Launch chamber body; A launch bay sealing cover, fastened to the launch bay body, to protect the parachute rocket housed within the launch bay body, the launch bay sealing cover comprising: Cover; A limiting hole is provided on the side of the cover facing the parachute rocket, configured to accommodate and limit the ignition head; Multiple limiting plates are evenly distributed along the circumference of the cover and extend from the edge of the cover toward the parachute rocket, configured to contact the sidewall of the rocket body of the parachute rocket to limit the rocket body.
6. The multi-arrow coordinated low-airspeed parachute deployment device according to claim 4, characterized in that, The ignition head is an electric ignition head, and the electric ignition heads of the multiple parachute rockets in the multiple launch chambers are configured to synchronously receive the start-up electrical signal in order to synchronously launch the multiple parachute rockets.
7. The multi-arrow coordinated low-airspeed parachute deployment device according to claim 4, characterized in that, The rope assembly also includes: Fireproof protective ring; The first rope connects the fireproof protective ring to the rope connector; The second rope connects the fireproof protective ring to the parachute pack; a portion of the second rope is folded and housed in the connecting compartment. The fireproof protection ring is configured to prevent the flame ejected by the flame nozzle from directly contacting the first rope and / or the second rope, and to break when subjected to an external force greater than a threshold.
8. The multi-arrow coordinated low-airspeed parachute deployment device according to claim 7, characterized in that, The fireproof protection ring includes: N first components and N second components are connected end-to-end to form a closed frame structure. The first components are connected to the rope connector via a first rope, and the second components are connected to the parachute via a second rope. Here, N is a positive integer and N≥3. A fracture structure is provided at the connection between the first component and the second component. The fracture structure is configured to break when the external force it receives exceeds a threshold, thereby separating the first component and the second component at the connection.
9. The multi-rocket coordinated low-airspeed parachute deployment device according to claim 1 or 2, characterized in that, The parachute compartment includes: Parachute bag warehouse body; The parachute compartment sealing cover is fastened to the parachute compartment body to protect the parachute housed in the parachute compartment body.
10. A low-altitude aircraft, characterized in that, The low-altitude aircraft includes the multi-arrow coordinated low-altitude parachute deployment device according to any one of claims 1 to 9.