AIR RESCUE SYSTEM

Description

TECHNICAL AREA

[0001] Rescue system for an aircraft based on a parachute. BACKGROUND

[0002] Parachute-based rescue systems for aircraft are known in the prior art. Aircraft can be, in particular, unmanned aerial vehicles or drones. Special requirements arise when the drone is a rotary-wing aircraft. With rescue systems for rotary-wing aircraft, it is particularly important to prevent the parachute and / or its lines from coming into contact with a rotor or other moving components of the rotor during or after deployment in an emergency situation, such that the rescue system is damaged and / or its overall function is negatively impaired. In conventional rescue systems, for example, a rescue parachute is forcefully propelled away from the rotor by a pyrotechnic charge.This allows the rescue parachute to deploy at a safe distance from the rotorcraft, reducing the likelihood of an unintentional collision between the parachute and its lines with the rotor. However, such rescue systems present a challenge because the pyrotechnic propellant is classified as hazardous material, requiring special precautions during the aircraft's design, certification, and operation. Retrofitting an aircraft with a pyrotechnic-based rescue system is therefore not without its problems.

[0003] JP 2021 091258 A discloses a technology that can reliably open a parachute in the event of a crash of an aircraft.

[0004] US Patent 5,836,544 A discloses a soft landing system for use in a rotorcraft, such as a helicopter. The system includes at least one parachute-containing structure that accommodates at least one parachute.

[0005] US 4 648 568 A reveals a braking parachute that is deployed at the rear of the helicopter in the event of a malfunction of the tail rotor.

[0006] GB 2 231 010 A discloses a parachute opening cover which includes means for tightening the cover around a cap in order to reduce sagging of the cap within the cover during the initial opening.

[0007] GB 2 014 095 A discloses a device for placing a packed parachute into a container. SUMMARY

[0008] The invention is defined by the independent claim. The dependent claims specify embodiments thereof.

[0009] The following is a simplified summary of some embodiments of the disclosure to provide a basic understanding of these embodiments and their advantages. Further embodiments and technical details are included in the detailed description below.

[0010] The present invention is based on the objective of providing a rescue system that prevents an aircraft from an uncontrolled crash and simultaneously ensures reliable deployment of the rescue system without being damaged by the aircraft. A further objective is to provide a rescue system designed in such a way that the flight characteristics of the aircraft are affected as little as possible when such a rescue system is retrofitted.

[0011] According to the invention, this problem is solved by a device according to claim 1. Further embodiments of the invention are set out in the respective dependent claims.

[0012] The rescue system according to the invention for an aircraft, which is a rotary-wing aircraft, comprises a main canopy with a main line and a plurality of main canopy lines, wherein the main line is designed to connect the main canopy to the aircraft on which the rescue system is installed. The system further comprises an outer container with a first diameter, which is designed to be arranged longitudinally on an outer surface of the aircraft along a tail boom of the rotary-wing aircraft, and an inner container, which is removably arranged in the outer container and is suitable for receiving the main canopy. The inner container is made of a lightweight, low-friction textile material.

[0013] Preferably, the inner container has a reefing area with a second diameter, wherein, by means of a plurality of loop-eyelet pairs, the second diameter of the reefing area is reefed substantially to a diameter smaller than the first diameter of the outer container when the main canopy is located inside the inner container, wherein a release line fixes the loops in the eyelets and thereby maintains the reefing of the inner container, and a line section, wherein the line section is arranged at a first end of the reefing area and is suitable for receiving the majority of the main canopy lines. Furthermore, a compression section is provided, wherein the third diameter is smaller than the second diameter and substantially corresponds to the reefed diameter of the reefing area. The compression section can preferably be arranged at a second end of the reefing area.Furthermore, the rescue system can have a device for attaching an auxiliary parachute, wherein the compression area can preferably be arranged between the device for attaching the auxiliary parachute and the reefing area.

[0014] Advantageously, the outer container can have a tubular structure and the inner container a tube-like shape, ensuring a secure arrangement of the inner container within the outer container. Such an arrangement of the inner container within the outer container, as described above, also has the advantage that the inner tube can be reliably removed from and opened by the outer container without risking damage to the rescue parachute during deployment or opening by parts of the aircraft.

[0015] In a preferred embodiment, the rescue system has an auxiliary parachute which is connected to the inner container by means of the auxiliary parachute attachment device and can thus ensure rapid deployment of the rescue parachute.

[0016] In another embodiment, the main line can be connected to the release line in such a way that the release line is only pulled out of the loop-eye pairs once the inner container has been completely pulled out of the outer container by the auxiliary parachute. This type of rescue parachute deployment is advantageous because the parachute remains reefed and can therefore be easily pulled out of the outer container until the inner container is completely free of the outer container and away from the aircraft before the rescue parachute is deployed.

[0017] Furthermore, the auxiliary parachute of the rescue system can advantageously be deployed purely mechanically, i.e., without the use of pyrotechnics. Purely mechanical deployment mechanisms are based, for example, on spring force or compressed air. Rescue systems that use a propellant, such as a rocket engine, to ensure that the rescue parachute is far enough away from the aircraft before deployment have the disadvantage that, while damage to the rescue parachute by the aircraft is avoided, this is accompanied by the risk of damage to the rescue parachute by the propellant itself.

[0018] In a further embodiment, the rescue system according to the invention can include an emergency detection module. Such a module enables precise monitoring of the aircraft's avionics, as well as a critical analysis of the acquired flight data, thereby enabling the creation of various emergency scenarios to minimize the risk of a false activation of the rescue system.

[0019] Preferably, the line compartment of the inner container can have multiple pockets suitable for holding the main canopy lines. Such an arrangement ensures secure stowage of the main canopy lines, which in turn guarantees reliable deployment of the reserve parachute.

[0020] In a preferred embodiment, the outer container can have a protective cap which, in the event of a detected emergency, is mechanically ejected from the outer container by the emergency detection module, for example, by means of a spring mechanism. Alternatively, the protective cap can be designed such that it is destroyed or bursts upon deployment of the auxiliary parachute by the pressure of the auxiliary parachute. Such protective caps are typically made of burstable foil. This prevents the risk of damage to the parachute or the aircraft by the protective cap and simultaneously ensures the safe stowage of the inner container within the outer container, wherein the aircraft is preferably a rotary-wing aircraft and the outer container is arranged longitudinally along a tail boom of the rotary-wing aircraft.

[0021] In a preferred embodiment of said rotary-wing aircraft, the main line can be connected to a rotor axis of the rotary-wing aircraft by means of a connection system, so that in an unfolded state of the main canopy, the main line of the main canopy is rotatably attached essentially near the center of gravity of the rotary-wing aircraft, thereby achieving a horizontal position of the rotary-wing aircraft in the deployed state of the rescue parachute and thereby reducing the risk of damage to the rotor or other parts of the rotary-wing aircraft. DESCRIPTION OF THE DRAWINGS

[0022] The preceding summary and the following detailed description of preferred embodiments are easier to understand when read in conjunction with the accompanying drawings. To illustrate the invention, the drawings show exemplary details of the described embodiments. The information presented in the drawings is for illustrative purposes only and does not limit the claimed invention.

[0023] The present invention is described in detail below with reference to the accompanying drawings: Fig. 1 shows a sketch that provides an overview of the rescue system, including an aircraft. Fig. 2 shows a schematic diagram of the rescue system. Fig. 3 shows an inner container for the main umbrella when packed. Fig. 4 shows details of the inner container for the main umbrella when packed. Fig. 5shows details of the inner container for the main umbrella in its unpacked state. Fig. 6A shows details of the reefing area of ​​the inner container for the main canopy in its unpacked state with loosened eyelets and loops. Fig. 6B shows details of the reefing area of ​​the inner container for the main canopy when packed with closed eyelets and loops. DETAILED DESCRIPTION

[0024] The present invention relates to a rescue system for an aircraft, as well as to a container for holding a parachute.

[0025] Aircraft in this context are manned or unmanned drones, for example, multi-rotor or single-rotor helicopters. Other aircraft for which the rescue system according to the invention is suitable include, for example, fixed-wing drones. Experiments with the rescue system according to the invention were conducted, for example, with a single-rotor helicopter drone with a maximum takeoff weight of 150 kg and a maximum speed of 140 km / h. However, the invention is not limited to application to this specific drone.

[0026] The rescue system according to the invention is based on the opening of a parachute and the resulting reduction in the drone's falling speed after the parachute has deployed in an emergency situation. This enables a relatively gentle landing of the aircraft after an emergency occurs.

[0027] Fig. 1shows an overview of the rescue system, including an aircraft.

[0028] In the left part of Fig. 1 The aircraft is shown as a single-rotor helicopter drone 130 with the main parachute 120 and pilot chute 110 deployed. The pilot chute 110 is smaller than the main parachute 120. The main parachute 120 is connected to the aircraft via a main line 125 and several suspension lines, or main parachute lines 128. The pilot chute 110 is connected to the main parachute 120 and the main parachute line 125 via a support line 115.

[0029] In the right part of Fig. 1Details of the rescue system's location are shown using the example of the single-rotor helicopter drone 130. The rescue system comprises an elongated, tubular outer container 135, which is arranged and mounted along a tail boom of the helicopter drone 130. This outer container 135 contains, among other things, an inner container and the main parachute 120 in its folded state (not in its deployed position). Fig. 1(shown). The longitudinal arrangement of the rescue system along the tail boom of the helicopter drone is aerodynamically advantageous and also beneficial in terms of weight distribution. This design feature of the rescue system, which enables this arrangement, makes the system particularly attractive for retrofitting drones. The outer container 135 is closed at the rear by a protective cover 136, which prevents the ingress of dirt and moisture during normal drone operation, i.e., not during emergency operations. The cover 136 can be a cap or a film, for example, a rupture film.

[0030] When the rescue system is triggered, this cover 136 is removed. This causes the auxiliary parachute 110, the inner container, and the main parachute 120 contained within it to be ejected and deployed. Details of this process are described below.

[0031] Optionally, the one that protrudes in the Fig. 1The arrangement shown extends the rear section of the tubular outer container 135 to or beyond a radius of the tail rotor. This has the advantage of reducing the probability that individual components of the rescue system will collide with the tail rotor during deployment and / or that their function will be impaired by the tail rotor.

[0032] Fig. 2 shows a schematic diagram of the rescue system and its details in the unactivated state.

[0033] The rescue system comprises an outer container 235 with a first diameter, which is arranged on the outside of the aircraft 130. This outer container 235 serves as a protective device for the other components of the rescue system described below. The elongated shape of the outer container is, as previously described, advantageous and is dictated by aerodynamics and the weight distribution during flight of the aircraft 130. However, the elongated shape of the outer container 235, and thus of the rescue system as a whole, is not without its problems with regard to the requirement that the triggering process, and consequently the deployment of the main parachute 220, must occur very quickly and reliably.

[0034] The outer container 235 is preferably made of a lightweight and durable material, such as an aluminum alloy or carbon fiber. The diameter of the outer container depends on the size of the parachute. The size of the parachute, in turn, depends on the drone's takeoff weight. Experience has shown that for a rescue system for drones with a maximum takeoff weight of 150 kg, a diameter of between 5 and 15 cm for the outer container is advantageous.

[0035] The rescue system further comprises an inner container 250, which in a non-triggered state is arranged in the outer container 235 and is suitable for receiving the main parachute 120.

[0036] The rescue system further comprises a main parachute 220 with a main line 225 and a plurality of suspension lines 228, hereinafter also referred to as main parachute lines, wherein the main line 225 connects the main parachute 220 to the aircraft 130 on which the rescue system is installed.

[0037] The main line 225 has a loop at the end installed on the aircraft, which is used as a loop coupling around the axis of a rotor head, specifically the axis of the central rotor of aircraft 130. Suspending the aircraft at the rotor head using the loop coupling principle has the advantage that the aircraft can land in a controlled manner on its landing gear, which effectively absorbs the energy of the landing impact. Alternatively, the rescue system can also be used without the loop coupling by allowing aircraft 130 to glide to the ground suspended at its tail.

[0038] Optionally, the section of the main line 225 furthest from the main parachute 220 is routed inside the aircraft 130, as described, and looped around the rotor axis. When the rescue system is deployed, the main line 225 comes under tension and releases predetermined breaking points on the fuselage of the aircraft 130, so that the aircraft 130 is fully tensioned with the main line 125, as shown in the left part of the Fig. 1 shown, and hangs vertically below the main canopy 120 when the main canopy is fully deployed.

[0039] Preferably, a rotatable coupling, called a swivel 229, is installed between the main line 225 and the main canopy lines 228. This coupling decouples the rotation of the aircraft's rotor 130 from the main canopy 220. In other words, due to the swivel 229, rotation of the rotor does not cause rotation of the main canopy lines 228 and the main canopy 220.

[0040] Fig. 2further shows an optional opening delay device 242, a so-called slider 242, which delays the deployment of the main parachute 220, especially at high speed of the aircraft, and enables controlled deployment of the main parachute 220.

[0041] Fig. 2 Figure 2 shows that the main canopy lines 228 are preferably stowed in line pockets 230. This packing method for the main canopy lines 228 allows for rapid deployment of the lines after activation of the rescue system and simultaneously prevents tangling. The inner container 250 is described in detail below.

[0042] The inner container 250 is a receptacle for receiving the main umbrella 220. The inner container 250 is preferably tubular and open at least at one end, where the main umbrella 220 is inserted into the receptacle.

[0043] The inner container is made of a lightweight, smooth-gliding textile fabric, for example, balloon silk.

[0044] The inner container 250, when not deployed, is stored inside the outer container 235. The inner container 250 is designed such that, upon deployment of the rescue device, it can escape very quickly and easily from the outer container 235 at the end of the released cover 236. The main parachute contained within the inner container 250 can also escape from the outer container 235. When packed, i.e., with the main parachute inside, the diameter of the inner container 250 is consistently smaller than the inner diameter of the outer container 235 along its entire length. This design ensures that the inner container, when packed, is easily movable within the outer container 235 and is not only moved into the outer container 235 after deformation. In other words, the inner container is not "crammed" into the outer container, but can be moved freely within the outer container when packed.with the main canopy contained, slide easily into the outer container and slide out upon deployment. A conventional parachute pack is, for example, cuboid or similar and differs significantly from the main canopy pack described herein, which is essentially an elongated cylinder with a substantially uniform but limited diameter (see . Fig. 3 ).

[0045] With known rescue parachutes, placing the rescue parachute in an outer, elongated storage container is problematic because achieving a uniform packing density along the entire length of the container is difficult. Therefore, when the rescue parachute is deployed, a safe and smooth escape of the main parachute from the storage container cannot be guaranteed. Placing the main parachute and packing it directly in the outer container 235 is also problematic. Achieving a uniform packing density of the main parachute 220 along the entire length of the outer container 235 is difficult, so a safe and smooth escape of the main parachute from the container cannot be guaranteed when the rescue system is deployed.The use of an inner container 250, according to the present invention, solves this problem and at the same time ensures optimal use of the interior space of the outer container 235, so that the rescue system as a whole can have a compact design.

[0046] To achieve the aforementioned shape characteristics of the main parachute packing using the inner container 250, it is advantageous for the inner container 250 to preferably comprise three areas, which are described in detail below. These areas may overlap. The three areas are arranged in the following sequence along the length of the inner container 250: line area 203, reefing area 205, and compression area 208.

[0047] The inner container 250 comprises the line compartment 203, which is suitable for accommodating a plurality of the main canopy lines 228. For this purpose, the line compartment 203 preferably includes the line pockets 230, which are attached and sewn to the outside of the inner container 250. When the rescue system is packed, bundles of sections of the main canopy lines 228 are stowed in these line pockets 230. The line pockets 230 are open at least on one side to allow the insertion of one or more lines.

[0048] As in Fig. 2 As shown, the line area 203 is arranged at a first end of the reefing area 205 and can optionally also overlap with the reefing area 205.

[0049] The inner container 250 further comprises the reefing area 205 with a second diameter, wherein, by means of a plurality of loop-eyelet pairs 280, the second diameter of the reefing area is reefed substantially to a diameter smaller than the inner diameter of the outer container 235 when the main canopy 220 is located within the inner container 250, a release line 285 fixing the loops in the eyelets and thereby maintaining a reef of the first container. Such a release line is also referred to as a "flex pin" or cotter pin. It is preferably made of a flexible, smooth material, for example, on nylon wire.

[0050] The majority of loop-eyelet pairs 280 along the reefing area 205 are arranged in pairs on the outside of the inner container 250 such that a loop can be fixed to a respective eyelet and the diameter of the inner container 250 in the reefing area 205 is reduced by reefing. The diameter of the reefing area 205 in the reefed state is smaller than the first diameter of the outer container 235. The diameter of the reefing area 205 in the unreefed state is larger than the inner diameter of the outer container 235.

[0051] The release line 285 serves to fix the majority of loops to the respective eyelets in such a way that removing the release line 285, for example by pulling it out, releases the fixation of the loop-eyelet pairs and increases the diameter of the inner container 250 in the reefing area 205 by means of an increase in diameter.

[0052] The inner container 250 further comprises a compression section (208, 308) with a diameter that is smaller than the diameter of the reefing section 205 in the unreefed state and that is substantially the same as the diameter of the reefing section in the reefed state and is smaller than the inner diameter of the outer container 235. The compression section 208 is arranged at an end of the reefing section 205 opposite the end at which the line section 203 is arranged.

[0053] The inner container further comprises a device 290 for attaching an auxiliary screen 210, wherein the compression area 208, as in Fig. 2The device 290 for attaching the auxiliary canopy 210 is arranged between the device 290 for attaching the auxiliary canopy 210 and the reefing area 205. The device 290 for attaching the auxiliary canopy 210 preferably allows a connection to an auxiliary canopy line. The auxiliary canopy 210, when packed, is preferably contained in an auxiliary canopy container 292. The auxiliary canopy container 292 can be, as shown in Fig. 2 shown, separate from the outer container 235. The cover 236 can preferably close the outer container 235 and the auxiliary screen container 292.

[0054] The deployment of the rescue system proceeds in the following steps: (a) An emergency detection module determines, for example by evaluating current sensor data, that an emergency situation exists and the rescue system should be deployed. (b) A control signal opens the cover 236, which is, for example, mechanically separated or folded away from the outer container 235. (c) The auxiliary parachute 210 is deployed by means of a mechanical ejection device; (d) the auxiliary parachute 210 opens; (e) the auxiliary parachute 210 pulls the inner container 250 out of the outer container 235 via the auxiliary parachute line 215; (f) the release line 285 is pulled at or shortly after the inner container 250 has been removed from the outer container 235, thus releasing the paired connections between loops and eyelets 280; (g) the reefing area 205 expands by impact; (h) the main umbrella 220 falls out of the inner container 250 due to gravity orThe inner container 250 is detached from the main canopy 220 by means of the auxiliary canopy 210 attachment device 290; in other words, the main canopy 220 is pulled out of the outer container 235 and subsequently out of the inner container 250 by the force of the auxiliary canopy 210; (i) the main canopy 220 deploys, possibly with a delay due to the optional slider 242; (j) the main line 225 of the main canopy 220 comes under tension, stretches vertically, releases predetermined breaking points on the fuselage of the aircraft 130, and puts the loop coupling under tension around the rotor axis; (k) the aircraft 130 descends to the ground, slowed by the main canopy 220 and the auxiliary canopy 210. Some successive steps in this sequence may also partially overlap.

[0055] Fig. 3Figure 1 shows the inner container 250 for the main canopy 220 in its packed state. The main line 325 connects the main canopy 220 to the glider 130. The release line 385 is connected to the main line 325 at one end. Pulling on the main line 325 pulls the release line 385 out of the loops 380, causing the loops to detach from the eyelets and releasing the reefing area 305. This release facilitates the separation of the inner container 350 from the main canopy 220 during the release process. Fig. 3Line area 303 is shown, with the filled line pockets visible from the outside. The reefing area 305 typically contains the larger portion of the lower canopy of the main parachute in terms of fabric volume. Reefing allows the diameter of this part of the inner container 350 to be reduced to a value smaller than the inner diameter of the outer container 235. The remaining parts of the folded main parachute, particularly its upper canopy, are stowed in the compression area 308. Furthermore, in Fig. 3 The device 390 for attaching the auxiliary screen 210 is shown. This device can be, for example, an eyelet or ring thimble that is attached to the fabric of the inner container 350.

[0056] Fig. 4Figure 1 shows a detail of the inner container 250 for the main parachute 220 in its packed state, as well as the main line 425 of the main parachute 220, the release line 485, and the combination 480 of eyelet and loop in its connected state. The sewn loops 481 are shown on the outside of the inner container 250, and the eyelets 482, sewn in pairs to the loops on the outside of the inner container 250, are also visible.

[0057] Fig. 5 shows the same section of inner container 250 as Fig. 4 , however, in the open, i.e., unpacked state. In the Fig. 5It is clearly evident that the diameter of the reefing area 505 in the unreefed state is significantly larger than the diameter of the compression area 508. It is also evident that the reefing area 505 partially overlaps the line area 503. The eyelets 580 are attached to the outside of the inner container 250 with a fabric strip 582. Opposite each eyelet, in pairs, is a loop 583, the continuation of which 581 is also sewn to the outside of the inner container 250.

[0058] Fig. 6A shows a detail of the eyelet 680, the sewn fabric band 682 and the corresponding loop 683 in the unreefed state of the reefing area.

[0059] Fig. 6BFigure 680 shows a detail of the eyelet 680, the sewn-on fabric band 682, and the corresponding loop 683 in the reefed state of the reefing area. It can be seen that the loop 683 is threaded through the eyelet 680, and the release line 685 is threaded through the end of the loop 683 that protrudes beyond the eyelet 683. The loop is thus held against the eyelet, maintaining the reefing of the inner container 250 filled with the folded main canopy 220. Pulling the release line 685 releases this paired connection between the opposite eyelet and loop, resulting in the reefing.

Claims

1. A rescue system for an aircraft (130) that is a rotorcraft, comprising: a main parachute (120) having a main line (125) and a plurality of main parachute lines (128), the main line (125) being adapted to connect the main parachute to the aircraft (130) on which the rescue system is installed; an outer container (135, 235) having a first diameter adapted to be disposed on an outer side longitudinally along a tail boom of the aircraft (130); an inner container (250) removably disposed in the outer container (135, 235) and suitable for receiving the main parachute (120); the rescue system being characterized in that the inner container (250) is made of lightweight, slidable textile fabric.

2. The rescue system of claim 1, wherein the main line (125) is adapted to be connected to a rotor axle of the rotorcraft by means of a connection system such that, in an unfolded state of the main parachute (120), the main line (125) of the main parachute (120) is rotatably secured substantially near the center of gravity of the rotorcraft.

3. The rescue system of claim 1 or 2, wherein the inner container (250) further comprises: a reefing portion (205, 305) having a second diameter, wherein, by means of a plurality of loop-eye pairs (280), the second diameter of the reefing portion is reefed substantially to a diameter that is smaller than the first diameter of the outer container (135, 235) when the main parachute is within the inner container (250), wherein a release line (285) fixes the loops in the eyes and thereby maintains reefing of the inner container (250); a line portion (203), the line portion being disposed at a first end of the reefing portion and suitable for receiving the plurality of main parachute lines (128); a compression portion (208, 308) having a third diameter, wherein the third diameter is less than the second diameter and substantially corresponds to the reefed diameter of the reefing portion, and wherein the compression portion (208, 308) is disposed at a second end of the reefing portion (205, 305); an apparatus (290, 390) for attaching an auxiliary parachute (110, 210), wherein the compression portion (208, 308) is disposed between the apparatus (290, 390) for attaching the auxiliary parachute and the reefing portion (205, 305).

4. The rescue system of claim 3, wherein the rescue system has an auxiliary parachute connected to the inner container by means of the apparatus for attaching the auxiliary parachute.

5. The rescue system of claim 3, wherein the main line is connected to the release line (285) such that the release line (285) is pulled out of the loop-eye pairs when the inner container has been pulled completely out of the outer container by the auxiliary parachute.

6. The rescue system of claim 4 or 5, wherein the auxiliary parachute (110) is ejected by means of a mechanical ejector.

7. The rescue system of any one of the preceding claims, wherein the rescue system has an emergency detection module.

8. The rescue system of any one of claims 3-7, wherein the line portion (203) has a plurality of pockets (570) suitable for receiving the main parachute lines (128).

9. The rescue system of any one of the preceding claims, wherein the outer container (135) has a protective cap (136) which is mechanically blasted away from the outer container (135) in a detected emergency.