29 results about "Drogue parachute" patented technology

An ejection seat includes an ejection seat sequencing system. The sequencing system enables time delays to various components of the system, such the drogue parachute, the main parachute, and harness release cartridge. A sequence controller receives data for a parameter, such as airspeed, from at least two sensors. The sequence controller selects a sequence timing delay mode to implement the time delays for the components of the sequencing system. The sequence controller also accesses a lookup table in a database accessible by the sequence controller. The sequence controller uses a delay parameter of the lookup table to modify a time delay within the sequence timing delay mode, as configured by a user.

An electronic drogue reefing release system includes a drogue parachute having a canopy, one or more reefing lines coupled to the canopy, one or more reefing line cutters coupled to the canopy, and one or more signal lines configured to deliver an electrical signal. The reefing lines are configured to restrict expansion of the canopy while in a first reefing state. The reefing line cutters are configured to place the at least one reefing line into a second reefing state in response to receiving the electrical signal so as to expand the canopy.

The application discloses a kind of umbrella resistance type elastic body nondestructive recovery device and method, belong to artillery launching technical field;The device includes projectile, and recovery body and deceleration parachute arranged in it;The projectile is the split type shell of non-fixed connection, in the state of holding tightly in artillery barrel, timely split after flying out of artillery barrel, eliminate the constraint of recovery body and deceleration parachute;The recovery body and deceleration parachute are connected by coupling assembly, the end of parachute rope of deceleration parachute is connected with the top end of recovery body by coupling assembly, and the parachute rope of deceleration parachute is arranged on recovery body along the set track, for the buffer connection between recovery body and deceleration parachute.The application solves the posture instability and parachute rope winding problem caused by the rigidity of deceleration parachute and recovery body, and does not need to design connecting mechanism and opening parachute mechanism separately, applies the object parachute system to the inside of elastic body in narrow space, guarantees that recovery body is not damaged by secondary overload impact and completes nondestructive recovery.

The application relates to a device and method for improving the opening reliability of a rescue parachute of an ejection seat, and relates to the field of air dropping. The device for improving the opening reliability of the rescue parachute of the ejection seat comprises a rescue parachute box and a deceleration parachute box which are installed on the ejection seat and are connected with each other, the deceleration parachute box is configured to be separable from the rescue parachute box, the rescue parachute box is internally provided with a rescue parachute, the deceleration parachute box is internally provided with a connecting belt, a deceleration parachute and a constant force breaking rope, one end of the connecting belt is connected with a parachute rope of the deceleration parachute, the other end of the connecting belt is connected with the top of the rescue parachute box, one end of the constant force breaking rope is connected with the top of a canopy of the deceleration parachute, the other end of the constant force breaking rope is connected with the top of the deceleration parachute box. The device and method for improving the opening reliability of the rescue parachute of the ejection seat solve the bending phenomenon of the parachute rope and the canopy during the high-speed ejection of the ejection seat, avoid the problems of early inflation of the rescue parachute, serious damage and local parachute turning, avoid the safety hazards caused by the interference after the separation of the parachute box and the rescue parachute, and improve the high-speed working reliability of the rescue parachute matched with the ejection seat.

This invention relates to an underwater self-floating unmanned aerial vehicle (UAV) swarm transport device and its operating process, comprising, from top to bottom, a top cover, an airbag compartment, a main body section, a tail section, and a deceleration parachute compartment. The top cover, main body section, and tail section are all externally covered with deep-sea buoyancy material. A transport device is located inside the main body section, comprising an UAV compartment, a battery compartment, and a control compartment. The UAV compartment carries the UAV system to ensure surface launch. The battery compartment and control compartment are located below the UAV compartment. The battery compartment provides power throughout the process, and the control compartment controls the device's movement and signal transmission and reception. A fixing ring is located at the bottom of the transport device for connecting an acoustic release device and a gravity anchor. This facilitates rapid and reliable transport and ascent of the UAV swarm, stable surface launch of multiple UAVs, and ensures operational reliability.

The invention discloses an unmanned aerial vehicle recovery system and method based on a fixing pin and an aerial vehicle, and the unmanned aerial vehicle recovery system based on the fixing pin comprises an ejection parachute cabin, a parachute cabin, a main parachute pack, a main parachute, a brake parachute, the fixing pin and a separation joint. The parachute bay is used for loading the ejection parachute bay, the parachute bay, the main parachute pack, the main parachute, the brake parachute, the fixing pin and the separation joint, the brake parachute is connected with the main parachute pack through a brake parachute connecting rope, the main parachute pack is connected with the main parachute through a main parachute connecting rope, and the main parachute pack is connected with the main parachute through a fixing pin. The main parachute is connected to the separating connector through a hanging belt, and the separating connector is connected with the unmanned aerial vehicle. The three-stage parachute opening process is achieved through the brake parachute, the main parachute and the corresponding main parachute closing opening, the requirement of the main parachute for materials is reduced, meanwhile, the separation connector is adopted to avoid winding of parachute cords, and the recycling stability is guaranteed.

This invention discloses a ramjet parachute deployment and load reduction system, comprising a restraint ring, a sliding sheet (3), a release belt (4), a second connecting belt (5), a first connecting belt (6), a deceleration chute (7), a release mechanism (8), a load-bearing belt (9), and a restraint rope (10). This system can extend the ramjet parachute's inflation and deployment time. Compared to the current two-stage deployment method, it reduces the impact of the deceleration chute (7) on the ramjet parachute's gliding performance, and does not lose the deceleration chute (7). Compared to the current sliding sheet closing method, it has a better load reduction effect.

A method, an apparatus, and an aircraft may include a hose reel configured to attach to a first end of a hose, wherein the hose may be further configured to wrap around the hose reel, and wherein the hose reel may be configured to spin. A drogue may be configured to attach to a second end of the hose. At least one spring coupled to the hose reel may be configured to provide a constant force, wherein the hose reel spins in a first direction to allow the hose to protract when the drogue receives a first force that is greater than the constant force of the at least one spring, and wherein the hose reel spins in a second direction to allow the hose to retract when the drogue receives a second force that is less than the constant force of the at least one spring.

This invention relates to a model aircraft deceleration parachute system, including a parachute cover, an unlocking assembly, and a servo motor. The servo motor controls a rocker arm to push the unlocking assembly away from the parachute cover. The unlocking assembly includes a switch push block, a rotating shaft, a rotating component, and a torsion spring. The switch push block has a switch mounting slot. The rotating component, in conjunction with the rotating shaft, is oscillatingly mounted within the switch mounting slot. The top of the rotating component has a torsion spring mounting slot. The rotating shaft passes through the torsion spring mounting slot, and the torsion spring, in conjunction with the rotating shaft, is positioned within the torsion spring mounting slot. The torsion arm of the torsion spring abuts against the bottom of the torsion spring mounting slot, and the torsion arm pushes the rotating component against one side of the switch mounting slot. This invention relates to a model aircraft deceleration parachute system where the servo motor controls the rocker arm to push the unlocking assembly to release it from the parachute cover. The unlocking assembly automatically resets under the action of a return spring. This invention, through its ingenious mechanical structure design, eliminates the need to reset the rocker arm before installing the deceleration parachute, improving the user experience.

This utility model relates to the field of military equipment technology, specifically to a parachute compartment assembly and clamping device, comprising a positioning plate, a lead screw fixedly mounted on the top of the positioning plate via a bearing seat, an internally threaded block threaded to the outer surface of the lead screw, a sliding column fixedly connected to the outer end face of the internally threaded block, and a parachute compartment disposed outside the sliding column for housing a deceleration parachute; a clamping block, comprising an expansion component for controlling the clamping block to expand outward to adapt to parachute compartments of various sizes, a filling component that automatically fills gaps in the expansion component when it expands outward, and a positioning component for locking the adjusted diameter of the expansion component. By setting up the clamping block, this utility model not only allows for the expansion or contraction of the clamping block without changing tooling when assembling parachute compartments of different sizes, flexibly adapting to parachute compartments of different diameters, but also automatically fills gaps generated during the expansion process, preventing uneven stress on the deceleration parachute.

The present application relates to the technical field of parachute application, in particular to a parachute system for cloud explosion bomb, which comprises a deceleration parachute, a main parachute, a cloud explosion bomb and a cloud cluster detonating device, the bottom of the main parachute is connected with the cloud explosion bomb, the multiple parachute ropes at the bottom of the deceleration parachute are connected with the top of the main parachute, the multiple parachute ropes at the bottom of the deceleration parachute enclose an installation space, an installation bag is arranged in the installation space, and the peripheral side of the installation bag is fixedly connected with the multiple parachute ropes of the deceleration parachute, the cloud cluster detonating device is arranged in the cavity of the installation bag, a connecting piece is connected with the installation bag, the connecting piece has a first state of closing the cavity and a second state of opening the cavity to form an opening, in the first state, the cloud cluster detonating device can be fixed in the cavity of the installation bag, and in the second state, the cloud cluster detonating device can enter and exit the cavity through the opening. The problem that the large parachute opening force in the prior art has an adverse effect on the safety of the detonating device is solved.

The invention discloses a novel air throwing device which comprises a brake parachute (1), a brake parachute pack (2), a binding belt (3) and a brake parachute connecting belt (4), the brake parachute pack (2) packages the brake parachute (1) and is fixed on the binding belt (3), and the brake parachute connecting belt (4) is connected with the brake parachute (1) and the binding belt (3). The parasol can be helped to separate the carrying bag in the air, the carrying weight of the parasol is reduced, the probability of rolling, dragging and other problems during landing of the parasol is reduced, and the safety of landing of the parasol is improved.

A brake parachute is additionally arranged on the basis of a main parachute, during recovery, the brake parachute is firstly opened to perform preliminary deceleration, so that the speed of the large high-speed unmanned aerial vehicle is reduced to be within a main parachute recovery envelope speed range, and then the main parachute is opened to complete further deceleration and stable landing. By means of the method, the recovery envelope can be greatly widened, meanwhile, the large impact load generated when the large-scale high-speed unmanned aerial vehicle is recovered is avoided, and recovery of the large-scale high-speed unmanned aerial vehicle is achieved.

The invention belongs to the field of aerospace engineering, and relates to a near space-oriented differential pressure self-expansion brake parachute and a parachute opening method and application thereof. A self-expansion parachute opening component is introduced, pre-filling gas is injected into all air pipes of the self-expansion parachute opening component in advance before a parachute body is packaged, and the air pipes are sealed, so that all the air pipes of the self-expansion parachute opening component can be quickly self-expanded by utilizing the internal and external pressure difference at the moment after the brake parachute is released out of a cabin in a near space, and the parachute body structure is quickly opened; therefore, automatic parachute opening is realized in a near-space low-dynamic-pressure environment. The technical limitation that a traditional brake parachute is unfolded depending on atmospheric dynamic pressure is broken through, the technical problem that the traditional brake parachute is difficult to unfold reliably and even cannot be unfolded in the near space is effectively solved, and the safety and reliability requirements of near space tasks can be met. The differential pressure self-expansion parachute opening technology is high in universality, suitable for various brake parachute configurations, high in designability and wide in application range, and application of the differential pressure self-expansion brake parachute in the aerospace field is promoted.

The application discloses a variable-resistance surface parachute and a parachute opening method, and relates to the field of parachutes. The variable-resistance surface parachute comprises a deceleration parachute, at least two groups of parachute lines connected to the deceleration parachute, a connecting belt corresponding to each group of the parachute lines, and at least one time-delay separator. Each group of the parachute lines is arranged at intervals along the circumference of the deceleration parachute, and the groups of the parachute lines are arranged at intervals along the radial direction of the deceleration parachute. One end of the connecting belt is connected to each parachute line in the corresponding group, and the other end is used for connecting the top of the parachute. The connecting belts corresponding to each group of the parachute lines on the inner side are connected to the top of the parachute through a time-delay separator respectively. The lengths of the connecting belts corresponding to each group of the parachute lines gradually increase from the inside to the outside, and the time-delay separators corresponding to each group of the parachute lines gradually cut off the corresponding connecting belts after a preset interval from the inside to the outside. The variable-resistance surface parachute and the parachute opening method provided by the application can adjust the opening area of the deceleration parachute by restraining the parachute lines to restrict the degree of full inflation of the canopy.

The invention discloses a group umbrella and main umbrella system suitable for large-tonnage reloading air-drop. The main umbrella system comprises a group umbrella system body formed by nine main umbrellas. The main parachute pack connecting rope is connected with the main parachute pack and connected with the main parachute through the parachute top damping connecting rope, the main parachute is connected with the main connecting rope through the main parachute connecting rope, and the brake parachute is connected with the main parachute connecting rope. According to the scheme, the large-tonnage traction capacity is achieved.

The application discloses a kind of folding wing cruise vehicle mounting and launching device and launching method, device is by launching barrel, force frame, hanging point, separation ring, control device, buffer pad, torsion spring hinge, guide frame, hatch control steering gear, hatch and mounting rack composition;The mounting and launching device reduces the aerodynamic interference between the folding wing cruise vehicle launching process and carrying platform, greatly improves the launching safety.And the mounting and launching device has no pyrotechnics and deceleration parachute, simple mechanism, safe, reliable, low cost, can be reused repeatedly;At the same time, its working process is given, and the launching device is opened, the folding wing cruise vehicle is separated from the launching barrel, the separation ring is unlocked, the separation ring is separated from the cruise vehicle, the cruise vehicle folding wing is unlocked and unfolded, the cruise vehicle enters the flight state, the separation ring is recycled, and the hatch is closed. The launching separation process completes the launching of the cruise vehicle.

The utility model belongs to the technical field of safety, and relates to a parachute opening device which is used for fixing a deceleration parachute pack of an unmanned aerial vehicle and pushing out and opening a deceleration parachute when needed, and is characterized by comprising a shell, an ignition tube seat and a cut-off piston are sequentially arranged in the shell from top to bottom, and a weak connecting position is reserved at the lower end of the shell. The lower end of the weak joint is provided with a connecting structure connected with an unmanned aerial vehicle parachute pack; an electric ignition tube is arranged in the ignition tube seat, and the electric ignition tube, the cut-off piston and an inner cavity of the shell form a narrow closed space; the cut-off piston can slide downwards along the inner wall of the shell and cut off the reserved weak connecting position. The parachute opening device can controllably separate and push out the parachute pack of the unmanned aerial vehicle; a mechanical separation structure is adopted, and gas and a large amount of heat are not discharged; gas production agents are not needed, so that the size is small, the weight is light, and the requirement for light weight of the unmanned aerial vehicle is met; only the electric ignition tube is used for starting, so that the reliability is high.

The embodiment of the invention provides an atmospheric vertical velocity measurement method and system based on a down-cast sonde, and is applied to the technical field of atmospheric physics. The method comprises the following steps: releasing the down-cast sonde from a flight platform in the air above a target observation area, and from the time when the down-cast sonde is released to the time when the down-cast sonde completes meteorological observation in the target observation area, keeping the down-cast sonde in an open state all the time, the falling process of the drop-down sonde is equivalent to the variable-deceleration falling motion of a rigid body composed of the brake parachute and the main body structure; the actual speed reduction of the down-cast sonde in the falling process is obtained; based on a ground reference system, decomposing the actual speed reduction of the down-cast sonde into an atmospheric vertical movement speed and a falling speed of the down-cast sonde in a static atmosphere; and performing inversion based on an inversion formula of the atmospheric vertical velocity to obtain the atmospheric vertical velocity. In this way, the weather vertical velocity can be directly obtained without relying on a ground station.

The utility model relates to a rope net for rejecting small ships, and belongs to the field of anti-terrorism stability-maintaining rejecting equipment, the rope net is formed by weaving nylon, polyester, aramid fiber and other materials, the rope net has the characteristics of light weight, strong flexibility, cutting resistance, good floatability and the like, and the front end of the rope net is provided with a quick connecting buckle. In actual use, the device can be quickly connected with a traction body cast and arranged by a traction rope net, and is launched through a special launching device; the brake parachute is arranged at the tail end of the rope net, after the brake parachute is thrown by the launching device, the brake parachute at the tail of the rope net is rapidly opened, the throwing speed of the rope net can be slowed down, and the rope net can be reliably arranged at a designated position. A plurality of floating balls are arranged at designated positions of the rope net, so that the rope net can reliably float when the rope net is opened and falls on the water surface, and small ships can be effectively intercepted and rejected.

The device comprises a shell, a cavity is formed in the shell, an energy absorption assembly and at least two pull rope assemblies are arranged in the cavity, the pull rope assemblies intersect at a first point position, the first point position is located at one end of the shell and used for being connected with the brake parachute, and the energy absorption assembly is arranged on the side, close to the first point position, of the cavity and used for being connected with the brake parachute. The side, opposite to the first point position, of the energy absorption assembly is connected with the shell through a pull rope assembly, so that when the brake parachute is opened, the pull rope assembly decomposes the pull force of the brake parachute and drives the energy absorption assembly to be compressed. The cavity is formed through the shell, the energy absorption assembly and the at least two pull rope assemblies intersecting at the first point position are integrated, the first point position is directly connected with the brake parachute, and the coherent load shedding logic of tension decomposition, stroke extension and energy absorption compression is achieved; the one-way impact load of the brake parachute is preliminarily decomposed through cooperation of a mechanical structure, the rope stroke is prolonged to reduce the peak load, the parachute body structure does not need to be changed, and compatibility is high.

This application discloses a deceleration separation device, comprising: a deceleration parachute compartment, a combined actuator, a deceleration parachute pack, a battery box, and a slave unit control board; the deceleration parachute compartment includes a compartment body and a compartment cover; a first port of the compartment body is snapped into the compartment cover; a second port of the compartment body is connected to the slave unit protective cylinder of a UAV via a first connector; the combined actuator is fixedly disposed inside the compartment body; one end of the combined actuator is a parachute ejector and connected to the compartment cover; the other end of the combined actuator is an explosive bolt and connected to the UAV's transition joint; the deceleration parachute pack is disposed inside the deceleration parachute compartment and connected to the compartment cover and the combined actuator via a second connector; the battery box is disposed inside the compartment body and connected to the parachute ejector and the explosive bolt; the slave unit control board is disposed inside the compartment body and communicatively connected to the parachute ejector and the explosive bolt. This application enables separation from the aircraft, reducing weight during free flight and improving the aircraft's endurance.

This invention relates to a disc-type folding loitering munition suitable for dense loading of large-caliber rockets, and pertains to the field of unmanned aerial vehicle (UAV) technology. It includes a mother missile, loitering munition bodies, a deceleration parachute, and a partition plate. The mother missile serves as the delivery carrier for the loitering munition bodies, responsible for long-range delivery. The loitering munition bodies are densely loaded in rows within the mission payload compartment of the mother missile, and are isolated and protected by the partition plate. The deceleration parachute is installed on the loitering munition body to decelerate the munitions after release, enabling them to reach normal operating speed. The loitering munition bodies of this invention can be densely loaded onto the mother missile, forming a swarm of loitering munitions after deployment, increasing firepower density and improving combat effectiveness. It is also suitable for loading large-caliber rockets, reducing onboard space occupation and improving usability. Furthermore, the tilt-rotor technology enhances the flight maneuverability of the loitering munitions.

The invention discloses a multipurpose air-drop type unmanned aerial vehicle honeycomb launching device, relates to the technical field of unmanned aerial vehicle launching equipment, and aims at solving the problems that an existing air-drop type unmanned aerial vehicle launching device is poor in load adaptability, insufficient in launching stability, low in structural reliability and weak in environmental adaptability. The device integrates a main cabin, a brake parachute cabin, a brake parachute, a throwing mechanism, an X-shaped folding wing and an unmanned aerial vehicle releasing mechanism. Descending speed buffering is achieved through the brake parachute, the X-shaped folding wings guarantee stable postures, the response time of the electromagnetic pin releasing mechanism is smaller than or equal to 0.1 s, and synchronous unlocking of multiple aircrafts is guaranteed. The adaptive unmanned aerial vehicle can carry various loads such as reconnaissance, strike and bait, can meet the rapid deployment and collaborative operation requirements of an unmanned aerial vehicle cluster in multiple scenes such as military strike, emergency rescue and area monitoring, has the characteristics of light weight, high reliability and reusability, is adaptive to various aerial launching platforms, and is wide in application range.

This invention proposes a reusable waterborne takeoff and landing space launch vehicle, belonging to the field of aerospace technology. It includes a rocket body, wing surfaces, tail fins, propulsion engines, attitude control engines, floats, mounting brackets, and a deceleration parachute release device. The rocket body has a pointed cylindrical shape and houses propellant, oxidizer, navigation, control, and energy supply equipment. Wing surfaces are mounted in pairs on both sides of the rocket body. Floats are symmetrically mounted on the wing surfaces on both sides. Tail fins are mounted in pairs on both sides of the tail section of the rocket body, and control surfaces rotating around the wing surfaces are mounted on the tail fins. A propulsion engine, consisting of a set of rocket engines and / or aero engines, is mounted at the end of the rocket body. A set of attitude control engines is symmetrically arranged at one end of the rocket body. The mounting bracket is axially positioned on the upper side of the rocket body. The deceleration parachute release device is mounted on the upper side of the rocket body and houses the deceleration parachute. This invention also proposes a method of use, solving the problems of high space launch costs and difficulty in increasing the maximum payload capacity.

The invention discloses a multi-mode cooperative emergency protection system and method for a personal aircraft, and relates to the technical field of personal safety protection, the multi-mode cooperative emergency protection system comprises an integrated protection garment body, an intelligent sensing and control unit and a multi-mode execution mechanism; the intelligent sensing and control unit and the multi-mode executing mechanism are both integrated on the integrated protective clothing body; the intelligent sensing and control unit is used for sensing and judging whether passengers and the personal aircraft are in an uncontrollable falling state or not in real time, a feasible escape solution is provided for the extreme working condition of low-altitude and short-time falling of the personal aircraft for the first time, effective speed reduction and posture stabilization are achieved within second-level time through the rapid inflation brake parachute, and the safety of the passengers is improved. The technical bottleneck that a traditional ejection umbrella is ineffective is overcome.

The utility model discloses a brake parachute separating structure, which relates to the technical field of brake parachutes and comprises a supporting frame, connecting supports are fixedly mounted on the left side and the right side of the bottom of the supporting frame, a mounting rack is mounted between the connecting supports, and the left end and the right end of the mounting rack are fixed through bolts. A first lock catch and a second lock catch are arranged in the middle of the upper end of the supporting frame, a lock ring is clamped between the first lock catch and the second lock catch, a lock rod is arranged above the lock ring, a lock sleeve is arranged at the top end of the lock rod, and the lock sleeve forms an aircraft mounting structure; a transmission impeller is installed on the front side of the right side of the supporting frame, a limiting frame is installed on the front side of the supporting frame, and the transmission impeller forms a transmission structure for rotation of the limiting frame. The brake parachute separation structure has the advantages of being simple in structure, rapid in separation, high in reliability, convenient to maintain and the like, and is suitable for brake parachute separation of spacecrafts, guided missiles and high-speed airplanes.

The utility model relates to an unmanned plane technical field provides a modularization combination deceleration umbrella, include: deceleration umbrella body, one side of deceleration umbrella body is provided with mounting mechanism, the mounting mechanism includes installation department and connecting assembly, connecting assembly sets up between installation department and deceleration umbrella body, the installation department is used for with unmanned plane connects, connecting assembly is used for with deceleration umbrella body connects, the utility model discloses a modularization combination deceleration umbrella, through setting up connecting assembly, when unmanned plane is about to land to ground, will electromagnetic block energization, and electromagnetic block produces the same magnetic pole with magnetic plate magnetism, at this time, electromagnetic block and magnetic plate are attracted, and the inclined surface block and the rectangular block are close to electromagnetic block, and the restoring spring is no longer restricted by the inclined surface block and begins to restore, drive the positioning rod to separate the inside of shell no.

The invention relates to an equivalent method for unfolding an interfering flow field brake parachute under Euler description, and belongs to the technical field of aircrafts. According to the method, the fluid grid is completely attached to the body, targeted encryption of the to-be-solved flow field is facilitated, high-precision flow field information is obtained, the parachute opening process is achieved under Euler description, combination of parachute opening, aircraft multi-body separation, weapon putting and other working conditions under a solver of Euler description is facilitated, and the parachute opening efficiency is improved. The working condition range capable of being analyzed by the solver is perfected, and the method can be suitable for fluid mechanics and fluid-solid coupling simulation calculation at the same time. When the solving problem is complex, by adopting the method and the computational fluid mechanics method, the introduction of a structure solver can be avoided while the analysis precision is ensured, and the analysis efficiency is greatly improved.