System for rapidly deploying stratospheric aerostat through guidance brake parachute

Abstract

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.

Description

Technical Field

[0001] The invention relates to the field of high-altitude aerostats, and in particular to a system for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute. Background Art

[0002] Near-space refers to the space range of 20 to 100 km above the ground. From the perspective of atmospheric stratification, the stratosphere is located within this altitude range. Near-space is between the operating altitudes of traditional aircraft and spacecraft. Due to the high technical difficulty, the research on near-space aircraft has been almost stagnant for a long time. It was not until recent years that the importance of near-space aircraft was recognized. Countries around the world have carried out research on near-space aircraft, and stratospheric aerostats are one of the research hotspots.

[0003] However, in the current development and testing of floating platforms at the bottom of near-space, the deployment of floating platforms basically requires a series of processes such as preparation before deployment, inflation of the aerostat on the ground, selection of a site for release, flying in the air, and fixed-point suspension. The instruments on the floating platform can then complete the collection of various data in the air; however, these processes have many restrictions on release conditions, high risks in the launch process, long deployment time, and difficulty in high-altitude fixed-point. In addition, the previous platform height adjustment was controlled by releasing ballast and exhausting helium. The ballast carried determined that its flight time was short, and the height changed dramatically during the adjustment process. It cannot meet the platform's rapid, safe, and accurate deployment tasks, nor can it meet the long-flight requirements of the floating platform. Summary of the invention

[0004] In order to quickly complete the deployment of an aerostat and save time on ground preparation procedures, the present application provides a system for quickly deploying a stratospheric aerostat by means of a guided deceleration parachute.

[0005] The present application provides a system for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute, which adopts the following technical solution:

[0006] A method for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute comprises the following steps;

[0007] S1. During the ground preparation stage, the floating platform, the floating balloon and the parachute connected in sequence are stored in the carrier cabin, with the parachute being the outermost part of the carrier cabin;

[0008] S2: Send the carrier capsule to the predetermined airspace, then unlock the parachute and detach from the capsule;

[0009] S3, changing the attitude of the deceleration parachute by adjusting the components to control the descent trajectory of the carrier cabin;

[0010] S4. After deceleration is completed, the floating balloon is unlocked and pulled out of the carrier cabin, and the floating balloon is inflated through the inflation assembly;

[0011] S5. After the inflation is performed for a predetermined time, the deceleration parachute is separated from the floating balloon;

[0012] S6. After the parachute is separated from the air balloon by a certain distance, the carrier cabin separates from the air balloon, and the air balloon and the air platform remain in the air to work;

[0013] S7. Recover the deceleration parachute and the transport cabin.

[0014] Optionally, the deceleration parachute includes a canopy and an adjustment platform, the canopy and the adjustment platform are connected by a plurality of parachute ropes, the adjustment platform is connected to the floating balloon by a sling, and the adjustment component is arranged on the adjustment platform. There are multiple groups of adjustment components, and each group of adjustment components is retracted and expanded for a single parachute rope to change the inclination state of the canopy.

[0015] Optionally, the adjustment component includes a roller and a motor, the roller is rotatably connected to the adjustment platform, one end of the umbrella rope is fixedly connected to the umbrella canopy, and the other end of the umbrella rope is wrapped and fixedly connected to the roller, and the motor is used to drive the roller to rotate to retract and extend the umbrella rope.

[0016] Optionally, the floating balloon includes an upper base and a lower base, which are connected by a balloon skin, and the balloon skin, the upper base and the lower base form an internally enclosed body; the sling is connected to the upper base, and the lower base is connected to the floating platform; the balloon skin is provided with an air inlet and an exhaust port, and the inflation assembly inflates the balloon skin through an inflation tube.

[0017] Optionally, a central reinforcement rope is provided between the upper base and the lower base, and two ends of the central reinforcement rope are respectively connected to the upper base and the lower base, and the length of the central reinforcement rope is less than the length of the balloon skin.

[0018] Optionally, a diaphragm is provided in the balloon skin, and the diaphragm and the balloon skin constitute a main airbag and a secondary airbag, the main airbag is located above the secondary airbag, the air inlet is arranged on the balloon skin of the main airbag, and the exhaust port is arranged on the balloon skin of the secondary airbag; the inflation assembly is connected to the air inlet and the exhaust port respectively through an inflation pipe.

[0019] Optionally, the balloon skin is connected to a tear strip, and two ends of the tear strip are respectively connected to the balloon skin and the inner wall of the carrier cabin.

[0020] Optionally, the inflation assembly includes a gas cylinder and an air compressor, the gas cylinder is fixedly connected in the carrier cabin, the gas cylinder is connected to the air inlet via an inflation pipe, and the inflation pipe is provided with an air inlet check valve; the air compressor is fixedly set on the floating platform, the compressor is connected to the exhaust port via an inflation pipe, and the mass of the air in the auxiliary airbag is adjusted by the operation of the air compressor, thereby adjusting the height of the entire floating platform.

[0021] In summary, this application includes the following beneficial technical effects:

[0022] 1. The system is equipped with a guided deceleration parachute, which is connected to the floating balloon through the parachute cabin. The parachute trajectory is controlled by the retraction and release of the parachute rope, so that the aerostat can be deployed quickly and safely, and the landing point accuracy is significantly improved. The parachute-balloon separation is performed after the floating balloon is inflated.

[0023] 2. A layer of diaphragm is used to separate the main airbag and the auxiliary airbag inside the floating balloon, which simplifies the structure and saves materials. A central sling is designed inside the balloon, and multiple tear strips are set on the outside of the floating balloon to ensure that the balloon will not be damaged due to overload during the parachute opening and inflation process.

[0024] 3. The system stores the guided deceleration device, inflation system and floating platform into a cabin, and uses an aircraft or rocket as a carrier to quickly throw the cabin into the high altitude of the target area; the cabin is decelerated by a guided deceleration parachute, and the inflation component in the cabin completes the inflation process of the floating balloon in the air. The aerostat and payload are kept in the air through separation measures, saving time for ground preparation procedures. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 This is a schematic diagram of the overall process of a method for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute according to the present application;

[0026] Figure 2 It is the overall structural diagram of the interior of the carrier cabin of the present application;

[0027] Figure 3 This is the overall structural diagram of the deceleration parachute of the present application;

[0028] Figure 4 This is the overall structure diagram of the floating balloon in the present application when it is not inflated;

[0029] Figure 5 It is an overall structural diagram of the floating balloon in the inflated state in this application.

[0030] Description of reference numerals:

[0031] 1. Carrier cabin; 2. Deceleration parachute; 21. Parachute body; 22. Parachute rope; 23. Adjustment platform; 24. Sling; 3. Floating balloon; 31. Upper base; 32. Lower base; 33. Balloon skin; 34. Center reinforcement rope; 35. Tear strip; 36. Diaphragm; 361. Main airbag; 362. Air inlet; 363. Auxiliary airbag; 364. Exhaust port; 37. Gas cylinder; 38. Inflation tube; 4. Floating platform. DETAILED DESCRIPTION

[0032] The following is combined with Figure 1-5 This application is described in further detail.

[0033] The embodiment of the present application discloses a method for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute 2. The method uses a special aerostat, which includes a carrier cabin 1, a floating balloon 3, a floating platform 4 and a deceleration parachute 2. The method includes the following steps:

[0034] S1. During the ground preparation stage, the floating platform 4, the floating balloon 3 and the deceleration parachute 2 connected in sequence are stored in the carrier cabin 1, and the deceleration parachute 2 is the outermost side of the carrier cabin 1;

[0035] The deceleration parachute 2 is connected to the floating balloon 3, and a floating platform 4 is suspended below the floating balloon 3. Various instruments for detecting air data are installed on the floating platform 4. The deceleration parachute 2 includes a canopy and an adjustment platform 23. The canopy and the adjustment platform 23 are connected by multiple parachute ropes 22. One end of the parachute rope 22 is connected to the adjustment platform 23, and the other end is connected to different positions of the canopy. The adjustment platform 23 is connected to the floating balloon 3 through a sling 24.

[0036] The floating balloon 3 includes an upper base 31 and a lower base 32, which are connected by a balloon skin 33. The balloon skin 33, the upper base 31 and the lower base 32 form an internally enclosed body; the sling 24 is connected to the upper base 31, and the lower base 32 is connected to the floating platform 4; an air inlet 362 and an exhaust port 364 are provided on the balloon skin 33, and an inflation component is provided in the carrier cabin 1, and the inflation component inflates the balloon skin 33 through an inflation pipe 38.

[0037] S2, sending the carrier cabin 1 to the predetermined airspace, and then unlocking the deceleration parachute 2 and separating from the cabin;

[0038] In this step, the deceleration parachute 2 is unlocked by a guide parachute, the purpose of which is to facilitate the opening of the parachute without the need for a power module. Before the deceleration parachute is deployed, the parachute compartment door is fixed by an electric lock; when unlocking, the electric lock is first triggered to open the parachute compartment door, and then the deceleration parachute is pulled out of the compartment by the guide parachute. This technology is an existing mature technology, and the relevant technology can be simply referred to the Chinese patent with publication number: CN216233005U.

[0039] S3, changing the attitude of the deceleration parachute 2 by adjusting the components to control the descent trajectory of the carrier cabin 1;

[0040] Specifically, a plurality of adjustment components for retracting and extending the parachute ropes 22 are arranged on the adjustment platform 23, and each adjustment component retracts and extends a single parachute rope 22 to change the tilt state of the parachute canopy.

[0041] The adjustment component includes a roller and a motor, the roller is rotatably connected to the adjustment platform 23, one end of the parachute rope 22 is fixedly connected to the parachute canopy, and the other end of the parachute rope 22 is wound and fixedly connected to the roller, and the motor is used to drive the roller to rotate to retract the parachute rope 22; after the parachute rope 22 is retracted, due to the asymmetry of the parachute canopy, the surface pressure on the inside and outside of the parachute canopy of the deceleration parachute 2 is no longer the same, the outer surface pressure of the parachute canopy on the rope-retracting side is lower than the inner surface pressure, and the outer surface pressure of the parachute canopy on the rope-releasing side is higher than the inner surface pressure, and finally a horizontal aerodynamic force is generated by the pressure difference, thereby achieving controllable descent trajectory.

[0042] S4, after deceleration is completed, the floating balloon 3 is unlocked and pulled out of the carrier cabin 1, and the floating balloon 3 is inflated by the inflation assembly;

[0043] The unlocking of the floating balloon 3 adopts high-altitude separation technology and uses a spring for cold separation. In the initial stage of separation, the pre-compression spring force plays a major role. After the floating platform leaves the cabin and the spring force disappears, the aerodynamic resistance difference is mainly used as the separation force to accelerate the separation of the cabin. The balloon is pulled out by separating the two cabin sections. This is an existing mature technology. For related technologies, please refer to the master's thesis "Research on the Dynamics of the Deployment Process of Arrow-borne Floating Platform" by Xiao Xiaobing of the National University of Defense Technology.

[0044] The floating balloon 3 includes an upper base 31 and a lower base 32, which are connected by a balloon skin 33. The balloon skin 33, the upper base 31 and the lower base 32 form an internally enclosed body; the sling 24 on the deceleration parachute 2 adjustment platform 23 is connected to the upper base 31, and the lower base 32 is also suspended and connected to the floating platform 4 through the sling 24; the balloon skin 33 is provided with an air inlet 362 and an exhaust port 364, and the inflation component inflates the balloon skin 33 through the inflation pipe 38.

[0045] At the same time, considering that the floating balloon 3 will bear a huge impact overload during the straightening process, and the balloon skin 33 material is relatively soft and thin, a central reinforcing rope 34 is designed inside the floating balloon 3 to bear the overload, and the overall length of the central reinforcing rope 34 is less than the length of the balloon skin 33. At the same time, multiple tear strips 3512 are arranged on the outside of the balloon to absorb the energy of the straightening process, and one end of the tear strip 3512 is fixed to the parachute cabin separation surface, and the other end is fixed to the equipment cabin. After completing the buffering process, the tear strip 3512 is peeled off from top to bottom into two sections, and after the balloon is filled, it is peeled off along with the guided deceleration parachute 2 and the balloon.

[0046] In order to enable the floating balloon 3 to change its altitude, a diaphragm 36 is provided in the balloon skin 33. The diaphragm 36 and the balloon skin 33 form a main airbag 361 and a secondary airbag 363. The main airbag 361 is located above the secondary airbag 363. The air inlet 362 is provided on the balloon skin 33 of the main airbag 361, and the air outlet 364 is provided on the balloon skin 33 of the secondary airbag 363. The inflation assembly is connected to the air inlet 362 and the air outlet 364 respectively through an inflation pipe 38.

[0047] The inflation assembly includes a gas cylinder 37 and a gas compressor. The gas cylinder 37 is fixedly connected to the carrier cabin 1. The gas cylinder 37 is connected to the air inlet 362 through the inflation pipe 38. The inflation pipe 38 is provided with an air inlet check valve. The gas compressor is fixedly arranged on the floating platform 4. The compressor is connected to the exhaust port 364 through the inflation pipe 38.

[0048] The gas cylinder 37 is inflated through the inflation pipe 38, and the rear of the inlet valve is heat-sealed to connect an air guide bag to prevent the high-pressure gas from directly impacting the balloon skin 33. The air compressor is the main actuator for the floating platform 4 to adjust the height. The auxiliary airbag 363 adjusts the mass of the air in the auxiliary airbag 363 through the operation of the air compressor, so that the height of the entire floating platform 4 is adjusted. In the unpowered floating platform 4 based on the use of the wind field, this height control measure is also the main actuator for the aerostat to perform regional residence and trajectory control.

[0049] S5, after the inflation is performed for a predetermined time, the deceleration parachute 2 is separated from the floating balloon 3;

[0050] It should be noted that the detachment of the deceleration parachute 2 and the floating balloon 3 is achieved by a cutter. After the inflation is performed for a predetermined time, the cutter cuts the sling 24 to achieve detachment. The detachment technology used in this step is a mature existing technology. For related technologies, please refer to the master's thesis "Research on the Dynamics of the Deployment Process of the Arrow-borne Floating Platform" by Xiao Xiaobing of the National University of Defense Technology.

[0051] S6, after the parachute 2 is separated from a certain distance, the carrier cabin 1 is separated from the floating balloon 3, and the floating balloon 3 and the floating platform 4 remain in the air to work;

[0052] Similarly, the separation of the carrier cabin 1 and the floating platform 4: the carrier cabin 1 and the floating platform 4 are connected by a separation nut. When separating, the separation nuts of the floating platform 4 and the carrier cabin 1 are unlocked, and the floating platform 4 and the carrier cabin 1 are separated. The relevant technology can also be simply referred to the master's thesis "Research on the Dynamics of the Deployment Process of Arrow-borne Floating Platform" by Xiao Xiaobing of the National University of Defense Technology.

[0053] S7, recovering the deceleration parachute 2 and the carrier cabin 1.

[0054] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. A method for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute, characterized in that The method comprises the following steps: S1. During the ground preparation stage, the floating platform, the floating balloon and the parachute connected in sequence are stored in the carrier cabin, with the parachute being the outermost part of the carrier cabin; S2: Send the carrier capsule to the predetermined airspace, then unlock the parachute and detach from the capsule; S3, changing the attitude of the deceleration parachute by adjusting the components to control the descent trajectory of the carrier cabin; S4. After deceleration is completed, the floating balloon is unlocked and pulled out of the carrier cabin, and the floating balloon is inflated through the inflation assembly; S5. After the inflation is performed for a predetermined time, the deceleration parachute is separated from the floating balloon; S6. After the parachute is separated from the air balloon by a certain distance, the carrier cabin separates from the air balloon, and the air balloon and the air platform remain in the air to work; S7. Recover the deceleration parachute and the transport cabin.

2. The method for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute according to claim 1, characterized in that: The deceleration parachute includes a canopy and an adjustment platform, the canopy and the adjustment platform are connected by a plurality of parachute ropes, the adjustment platform is connected to the floating balloon by a sling, the adjustment component is arranged on the adjustment platform, and there are multiple groups of adjustment components, each group of adjustment components is retracted and extended for a single parachute rope to change the inclination state of the canopy.

3. The method for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute according to claim 2, characterized in that: The adjustment component includes a roller and a motor. The roller is rotatably connected to the adjustment platform. One end of the umbrella rope is fixedly connected to the umbrella canopy, and the other end of the umbrella rope is wound and fixedly connected to the roller. The motor is used to drive the roller to rotate to retract and extend the umbrella rope.

4. The method for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute according to claim 3, characterized in that: The floating balloon includes an upper base and a lower base, which are connected by a balloon skin. The balloon skin, the upper base and the lower base form an internally enclosed closed body; the sling is connected to the upper base, and the lower base is connected to the floating platform; an air inlet and an exhaust port are provided on the balloon skin, and the inflation component inflates the balloon skin through an inflation tube.

5. The method for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute according to claim 4, characterized in that: A central reinforcement rope is provided between the upper base and the lower base, and two ends of the central reinforcement rope are respectively connected to the upper base and the lower base, and the length of the central reinforcement rope is less than the length of the balloon skin.

6. A method for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute according to claim 5, characterized in that: A diaphragm is provided in the balloon skin, and the diaphragm and the balloon skin constitute a main airbag and a secondary airbag. The main airbag is located above the secondary airbag, the air inlet is provided on the balloon skin of the main airbag, and the exhaust port is provided on the balloon skin of the secondary airbag; the inflation assembly is connected to the air inlet and the exhaust port respectively through an inflation pipe.

7. A method for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute according to claim 6, characterized in that: The balloon skin is connected with a tear strip, and two ends of the tear strip are respectively connected to the balloon skin and the inner wall of the carrier cabin.

8. The method for rapidly deploying a stratospheric aerostat by guiding a deceleration parachute according to claim 7, characterized in that: The inflation assembly includes a gas cylinder and an air compressor. The gas cylinder is fixedly connected in the carrier cabin, and is connected to the air inlet through an inflation pipe. The inflation pipe is provided with an air inlet check valve. The air compressor is fixedly arranged on the floating platform, and is connected to the exhaust port through an inflation pipe. The mass of the air in the auxiliary airbag is adjusted by the operation of the air compressor, thereby adjusting the height of the entire floating platform.

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