60 results about "Drogue parachute" patented technology

The utility model relates to a model airplane brake parachute mechanism which comprises a brake parachute cabin body, a brake parachute pack, a parachute pack ejection device, a parachute pack cover plate, an unlocking assembly and a steering engine, the brake parachute cabin body is provided with a parachute pack groove for containing the brake parachute pack, the parachute pack ejection device is arranged at the groove bottom of the parachute pack groove, the brake parachute pack is placed on the parachute pack ejection device, and the steering engine is arranged on the brake parachute cabin body. The parachute pack ejection device provides thrust to abut the deceleration parachute pack against the parachute pack cover plate, the parachute pack cover plate capable of opening or closing the parachute pack groove is arranged at an opening of the parachute pack groove, the unlocking assembly is arranged on the deceleration parachute cabin and connected with the parachute pack cover plate in a matched mode, and the steering engine is arranged on the deceleration parachute cabin and connected with the parachute pack cover plate in a matched mode. The steering engine can control the rocker arm to push the unlocking assembly to leave the parachute pack cover plate, so that the parachute pack cover plate opens the parachute pack groove.

A method is disclosed herein. The method includes receiving, by a processor, an ejection command for ejecting an ejection seat from an aircraft; determining, by the processor, an airspeed and an altitude of the ejection seat; responsive to the altitude of the ejection seat indicating a second mode of operation, determining, by the processor, whether the airspeed of the ejection seat is at or above a first threshold and below a second threshold; and responsive to the airspeed of the ejection seat being at or above the first threshold and below the second threshold: sending, by the processor, a command to deploy a drogue parachute; and, responsive to a first predetermined time period expiring, sending, by the processor, a command to deploy a main parachute and sever the drogue parachute based on a variable drogue severance delay.

A method is disclosed herein. The method includes receiving, by a processor, an ejection command for ejecting an ejection seat from an aircraft; determining, by the processor, an equivalent airspeed and an equivalent altitude of the ejection seat; and, responsive to the airspeed and the altitude indicating a second mode of operation: sending, by the processor, a command to deploy a drogue parachute; determining, by the processor, a variable drogue severance delay; and responsive to the variable drogue severance delay expiring, sending, by the processor, a command to sever the drogue parachute and deploy a main parachute.

The invention relates to a low-cost parachute landing recovery system for a microgravity load return capsule, and aims to realize an efficient, reliable and economical recovery scheme through modular design, all modules are connected through standard interfaces, and assembly, maintenance and upgrading are facilitated. The structure module is used for assembling the parachute module and providing necessary shock resistance; the parachute module is used for pneumatic deceleration and attitude stabilization of the system and adopts a multi-stage unfolding structure; and the initiating explosive device module is used for bouncing the brake parachute, releasing the brake parachute and releasing a parachute closing opening. According to the system, the production and maintenance cost is remarkably reduced through modular design, meanwhile, the reliability and adaptability of the system are improved, and the system is suitable for various microgravity load return scenes and has wide market application prospects.

The invention discloses a series brake parachute system which comprises a main parachute, a brake parachute and at least two connecting ropes, and a parachute top hole is formed in the parachute top of the main parachute; the area of the brake parachute after being inflated is smaller than the area of the parachute top hole after the main parachute is inflated; and one end of each connecting rope is connected with the parachute top of the main parachute. The main parachute has the advantages that part of airflow entering the main parachute flows to the rear of the center of the main parachute through the parachute top hole, it is guaranteed that the airflow field behind the center of the main parachute is good, and conditions are provided for normal inflation and stability of the brake parachute; the length of each connecting rope can be greatly reduced, fluctuation similar to ship movement caused by the fact that the connecting ropes are too long is avoided, inflation stability of the series parachute system is guaranteed, the overall length of the series parachute system is greatly reduced, and the weight of the series parachute system is reduced.

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 invention provides a composite brake parachute for an aircraft, and belongs to the technical field of aircraft landing deceleration, the composite brake parachute specifically comprises a first parachute body, a plurality of second parachute bodies, a first connecting rope and a plurality of second connecting ropes, the first parachute body is connected with the tail of the aircraft through the first connecting rope, and the second parachute bodies are mutually connected through the second connecting ropes; the umbrella cloth of the first umbrella body is connected with the umbrella rope of the second umbrella body through a second connecting rope. According to the treatment scheme, the requirement for the structural strength of a single brake parachute material is lowered while the speed reduction effect and reliability of the brake parachute are improved.

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.

A digital meteorological data monitoring device for artificial hail suppression operation relates to the field of aerial meteorological data monitoring and is used for eliminating potential safety hazards caused by high-speed falling of the digital meteorological data monitoring device. The digital meteorological data monitoring device for the artificial hail suppression operation comprises a digital meteorological data monitoring shell, a lift-off balloon, brake parachute cloth, a connecting rope and a trigger assembly, a plurality of mounting lug plates are arranged on the upper side wall of the digital meteorological data monitoring shell, a containing groove is further formed in the side wall of one side of the digital meteorological data monitoring shell, and the containing groove is formed in the middle of the side wall of one side of the digital meteorological data monitoring shell; the lift-off balloon is arranged above the digital meteorological data monitoring shell and is connected with the plurality of mounting lug plates; the brake parachute cloth is arranged in the accommodating groove; the number of the connecting ropes is multiple, one end of each connecting rope is connected to the edge of the brake parachute cloth, and the other end of each connecting rope is fixedly connected with the inner wall of the digital meteorological data monitoring shell.

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.

An embodiment of the present invention discloses a braking system for a slide rail test. The braking system includes two slide rails arranged in parallel and a trolley disposed on the two slide rails; it further includes a deceleration component, and the deceleration component includes a first collar sleeved on the slide rail and a deceleration parachute connected to the first collar; the deceleration component is configured such that when the trolley impacts the first collar and drives the first collar to move along the extension direction of the slide rail, the deceleration parachute unfolds to slow down the movement speed of the trolley. The braking system provided by this embodiment can safely decelerate a trolley moving at high speed to a stop, avoid the trolley hitting the terminal facilities of the slide rail, resulting in the flying off of trolley components from the slide rail and causing damage to personnel and buildings, ensure the safety of the trolley and on-vehicle equipment, meet the working requirements of the slide rail test, and provide a method for safe deceleration braking for the slide rail test.

The invention discloses a throwing type sediment in-situ testing device and method, and belongs to the technical field of geotechnical testing equipment.The throwing type sediment in-situ testing device comprises a probe, a feeler lever, a control cabin and a hanging ring which are sequentially arranged from bottom to top, a signal receiving and transmitting assembly comprises a sliding rod, a transceiver and a connecting line, the sliding rod is movably connected with the control cabin, and the transceiver is connected with the connecting line. The transceiver is arranged at the top end of the sliding rod, one end of the connecting line is connected with the sliding rod, and the other end of the connecting line is connected with an unmanned aerial vehicle; the speed reducing mechanism comprises a speed reducing parachute and a driving assembly, the speed reducing parachute comprises a framework and parachute leaves, the framework is rotationally connected with the control cabin, one end of each parachute leaf is connected with the control cabin, the other end of each parachute leaf is connected with the framework, and the driving assembly can drive the framework to extend towards the periphery of the control cabin to drive the parachute leaves to be unfolded. The throwing type sediment in-situ testing device is adopted in the throwing type sediment in-situ testing method. The umbrella leaves play a role in speed reduction, so that the probe is prevented from being greatly impacted when penetrating into the soil body.

The invention relates to a tail end separation type secondary detonation cloud explosive bomb combat guiding matching control method, and belongs to the technical field of cloud explosive warheads. The method comprises the following steps: step 1, when the tail end of the fuel-air explosive warhead reaches a preset height, binding delay time (delta T1) for a fuse of the primary fuel-air explosive warhead, binding delay time (delta T2) for a secondary detonation cabin, separating the fuel-air explosive warhead from the secondary detonation cabin through a separating device, enabling the fuel-air explosive warhead to continuously fly forwards, and setting delay time (delta T2) for the fuse of the primary fuel-air explosive warhead; the secondary detonating cabin is connected with a brake parachute for decelerating flight; 2, the fuze of the primary fuel-air explosion warhead explodes according to the preset delay time, the fuel-air explosion agent is thrown, cloud clusters are formed, the cloud cluster forming time is recorded as delta T, and meanwhile the secondary detonation cabin continues to move downwards; and 3, when the secondary detonation cabin falls into the cloud cluster in the step 2 and detonates according to the preset delay time to form cloud detonation, and the target is damaged. The combat attraction matching control method can adapt to the supersonic speed condition, the process action time is in the millisecond level, environment interference can be effectively reduced, and reliability is improved.

The invention discloses a brake parachute packing device and method.The brake parachute packing device comprises a rack, a variable parachute cylinder and a thrust component, the thrust component is arranged on the rack, the movable end of the thrust component is connected with a pressing plate, the pressing plate is arranged above the variable parachute cylinder, and the thrust component drives the pressing plate to move up and down and is used for extruding a brake parachute in the variable parachute cylinder; the variable umbrella barrel comprises a top frame, a plurality of supporting rods evenly distributed in the circumferential direction of the top frame and a bottom separating and gathering component used for driving the supporting rods to gather or separate and open, the lower ends of the supporting rods are connected with the bottom separating and gathering component, and the upper ends of the supporting rods are connected with the top frame. The bottom separating and gathering part drives the supporting rods to move in the radial direction of the top frame. According to the invention, rapid packaging of the brake parachute and rapid adaptation of packaging of different parachute types are realized, the maintenance efficiency of ground crew is improved, and the device is especially suitable for packaging of drag parachutes.

The invention relates to an aerocar brake parachute system, a control method and an aerocar, the aerocar brake parachute system comprises a car body, a propeller, a brake parachute, an air suspension unit and a control unit, the propeller is arranged at the top of the car body and comprises a containing cavity, and the brake parachute is arranged in the containing cavity; the air suspension unit is used for driving the brake parachute to pop out of the containing cavity and be opened through compressed air under the action of a control signal of the control unit. The brake parachute system of the hovercar drives the brake parachute through compressed air of the air suspension unit of the hovercar, so that the reliability of the brake parachute and the safety of the hovercar can be greatly improved.

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.

The invention discloses a method for rapidly deploying a stratospheric aerostat through a guidance brake parachute. Relates to the field of high-altitude aerostats. The method comprises the steps that S1, in the ground preparation stage, a floating platform, a floating balloon and a brake parachute which are connected in sequence are contained in a carrying cabin, and the brake parachute is located on the outermost side of the carrying cabin; s2, the carrying cabin body is conveyed to a preset airspace, and then the brake parachute is unlocked and separated from the cabin body; s3, the posture of the brake parachute is changed through an adjusting assembly so as to control the descending track of the carrying cabin body; s4, after speed reduction is completed, the floating air ball is unlocked and pulled out of the carrying cabin, and the floating air ball is inflated through an inflation assembly; s5, after inflation is performed for a preset time, the brake parachute is separated from the floating air ball; s6, after the brake parachute is separated from a certain distance, the carrying cabin is separated from the floating air ball, and the floating air ball and the floating platform are left in the air to work; s7, recovering the brake parachute and the carrying cabin body; according to the system, a guidance speed reduction device, an inflation system and a floating platform are contained in a cabin, and an aircraft or a rocket serves as a carrier to rapidly throw the cabin to the high altitude of a target area; the cabin body decelerates through the guidance brake parachute, the inflation assembly in the cabin completes the inflation process of the floating balloon in the air, the aerostat and the effective load stay in the air through a separation measure, and the time for preparing procedures on the ground is saved.

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 invention provides a stand column structure for a brake parachute rocket sled with large load and large overturning moment. The stand column structure mainly solves the problem that an existing stand column structure formed by welding a supporting plate and a sealing plate cannot meet the requirement for the erection height of a large-load and large-overturning-moment brake parachute test. According to the scheme, a three-layer structure composed of a front stand column set, a middle stand column set and a rear stand column set is included, side rods are arranged between the layers for reinforcement, and a transverse rod and a vertical rod are arranged between the two measuring rods of the front stand column set and the rear stand column set and used for reinforcing the overall bearing capacity; a triangular flow structure is arranged on the windward side of the stand column structure. Compared with common stand columns, the number and distribution of the whole stand columns are increased, and the requirements for large loads and large overturning torque are met; meanwhile, a triangular rectification structure is additionally designed, so that the airflow field distribution of the skid body is optimized, and the aerodynamic resistance of the skid body is reduced.

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.

The utility model provides a movable brake parachute mounting ladder which solves the problems that when a brake parachute is folded and stored through a brake parachute mounting ladder, an operator can not turn around and move conveniently, and efficiency is low. The device comprises a moving device capable of moving on the ground, a supporting bottom frame is arranged at the top of the moving device, a standing platform is arranged at the top of the supporting bottom frame, and the standing platform comprises a plurality of platforms which are sequentially stacked and installed from bottom to top. The area of the platform on the upper layer is smaller than that of the platform on the lower layer, so that the standing platform forms a multi-layer stepped structure; first vertical rods are fixedly arranged on the left side and the right side of the supporting bottom frame correspondingly, and fireproof heat insulation lifting devices extending in the front-back direction are fixedly arranged on the tops of the first vertical rods on the left side and the right side correspondingly. When the brake parachute is used, the multi-layer step-shaped standing platform is adopted, the use requirements of operators with different heights can be met, and the operators can freely move and turn around on the standing platform when folding and storing the brake parachute.

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 model airplane brake parachute system comprises a parachute pack cover plate, an unlocking assembly and a steering engine, the steering engine can control a rocker arm to push the unlocking assembly to leave the parachute pack cover plate, the unlocking assembly comprises a switch push block, a rotating shaft, a rotating piece and a torsional spring, and a switch mounting groove is formed in the switch push block; the rotating piece is matched with the rotating shaft to be installed in the switch installation groove in a swinging mode, a torsion spring installation groove is formed in the top of the rotating piece, the rotating shaft penetrates through the torsion spring installation groove, the torsion spring is matched with the rotating shaft to be arranged in the torsion spring installation groove, a torsion arm of the torsion spring abuts against the groove bottom of the torsion spring installation groove, and the torsion arm pushes the rotating piece to abut against one side of the switch installation groove. According to the model airplane brake parachute system, a rocker arm is controlled by a steering engine to push an unlocking assembly to unlock a parachute pack cover plate, and the unlocking assembly automatically resets under the action of a reset spring. Through the ingenious mechanical structure design, the brake parachute pack can be installed without resetting the rocker arm, and the use experience of a user is improved.

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.