CN116142491A - Full-speed-domain multiple deceleration descending system of flexible umbrella cone assembly and control method - Google Patents
Full-speed-domain multiple deceleration descending system of flexible umbrella cone assembly and control method Download PDFInfo
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Abstract
A full-speed-domain multiple deceleration descending system of a flexible parachute cone assembly and a control method thereof are provided, wherein the descending system comprises an aircraft structure, a flexible inflatable cone, a connecting and separating structure and a parachute device, the descending system is arranged on a ship along with a freight aircraft in a furled state, a descending load is placed in a load cabin of the descending system on the orbit by an astronaut, the descending system is arranged on an outer hanging point of a space station cabin or a butt joint channel cabin door of the space station, the descending system is separated from the space station at a certain speed by an ejection separating device, track-changing braking and autonomous posture-adjusting are carried out after a specified distance is separated, track-leaving braking is completed, a track-throwing control cabin is carried out after a return posture is established, the track-returning control cabin enters a return track in a preset reentry posture, is inflated and unfolded into an inverted cone shape before entering the atmosphere, the track is decelerated and stably descended after entering the atmosphere, pneumatic heating and overload are carried out in the reentry process, the landing speed is further reduced by adopting a parachute to realize safe landing, the landing speed is equivalent to the landing speed of a return satellite, and the effective load safety is ensured.
Description
Technical Field
The invention relates to a full-speed-domain multiple deceleration descending system of a flexible umbrella cone assembly and a control method, and belongs to the technical field of entering, decelerating and landing of spacecrafts.
Background
With the complete establishment of space stations in China, the space stations enter normal operation and application, and a large amount of space science experiment payloads face the downlink requirement. According to the conservation estimation of the space station scale in China, the downlink demand during operation can reach hundreds of kilograms each year, and the limited downlink capacity and the downlink frequency of two times each year of the Shenzhou airship cannot meet the requirements. The downlink capacity of the space station comprises load weight, downlink frequency and downlink cost, and if the downlink capacity of the space station is insufficient, the comprehensive operation benefit of the space station is seriously affected, and the space station is restricted to play a role in promoting national technical progress and economic development. Therefore, the development of flexible, efficient and economic means for descending transportation of goods in space stations is urgently needed, and the urgent demands of descending of a large number of payloads in space stations in China with high frequency and low cost are met.
Disclosure of Invention
The invention solves the technical problems that: aiming at the lack of a downlink system design capable of meeting the high-frequency and low-cost downlink of a large number of payloads of a space station in the prior art, a full-speed domain multiple deceleration downlink system of a flexible umbrella cone assembly and a control method are provided.
The invention solves the technical problems by the following technical proposal:
the full-speed-domain multiple deceleration descending system of the flexible parachute cone assembly comprises an aircraft structure, a flexible inflatable cone, a connecting and separating structure and a parachute device, wherein the aircraft structure comprises a rigid nose cone, a control cabin, a load cabin and a attitude control cabin, the rigid nose cone is arranged at the head of the aircraft structure and is used for bearing standing point temperature and standing point pressure in the reentry descending process of the aircraft structure, the flexible inflatable cone is arranged at one side of the rigid nose cone, which is close to the tail of the aircraft structure, and is used for bearing aerodynamic force and thermal load in the return process of the aircraft structure so as to realize pneumatic deceleration, the control cabin is arranged at one side of the rigid nose cone, which is close to the tail of the aircraft structure, for carrying out energy supply and full-flight-stage control on the aircraft structure, the load cabin is used for carrying out mass center adjustment balancing on the aircraft structure and is arranged at one side of the control cabin, which is close to the tail of the aircraft structure, and the attitude control cabin is arranged at the tail of the aircraft structure, and the attitude control cabin is matched with the control cabin for carrying out attitude control and off-track braking on the aircraft structure and maintaining stable attitude of the aircraft structure; the connection and disconnection structure is used for connecting the aircraft structure with the external space station; the parachute device is arranged at the axial center position of the load cabin before opening the parachute, and recovery and deceleration of the aircraft structure after opening the parachute are realized.
The remote measuring and marking device is arranged in the control cabin and is used for realizing measurement and control and marking of the whole working stage of the aircraft structure and carrying out data feedback.
The rigid nose cone is of a rigid heat-proof structure, the edge of the rigid nose cone is connected with the minimum ring bag body of the inflation system of the flexible inflation cone through a pressing strip, the load cabin is used for installing a payload, the load cabin is subjected to descending packaging loading through a side wall opening, the side wall is divided into three parts, one part is a fixed cabin wall which is not movable or rotates, the other two parts are rotatable cabin doors which rotate around cabin door shafts respectively, when the rotatable cabin doors are closed, the cabin doors can be automatically locked, the cabin doors are closed, when the rotatable cabin doors are opened, the rotatable cabin doors are opened by pulling a pull pin, a cable special channel is arranged in the center of the load cabin, and the cable arrangement requirement of all cabin sections is provided for the aircraft structure.
The load cabin is used for adjusting and balancing the mass center of the system after loading the load through the mass center inertia automatic balancing mechanism, and the mass center inertia automatic balancing mechanism is installed through the control cabin; the flexible inflatable cone comprises an inflatable cone body, a thermal protection skin and a packaging structure, wherein the inflatable cone body is formed by stacking and intersecting circular rings after being unfolded, the circular rings are communicated with each other, the thermal protection skin consists of an ablation-resistant layer, a heat insulation layer and a bearing layer, and the ablation-resistant layer is made of a high-temperature-resistant fiber fabric and a heat-resistant coating and is used for bearing external airflow scouring and pneumatic heat flow; the heat insulation layer blocks heat from being transferred to the inside, and the temperature of the internal air-blocking bearing layer and the temperature of the return cabin structure are protected to be in a usable range; the bearing layer is made of a bearing fabric film-coated material and is used for preventing external high-temperature gas from flowing into the structure through the gaps, and the bearing fabric is used for bearing and transmitting pneumatic load on the surface of the structure.
The flexible inflation cone is internally provided with an inflation assembly, the inflation assembly is installed through a control cabin and comprises a high-pressure gas cylinder, a normally closed electric explosion valve, a normally closed electromagnetic valve and an air pressure sensor, when the flexible inflation cone is unfolded, an external sealing rope is cut off, the normally closed electromagnetic valve and the normally closed electric explosion valve are opened to inflate the inflation cone, the inflation cone drives a thermal protection skin to be unfolded in place and provides pretightening force for the thermal protection skin, the normally closed electromagnetic valve is closed when the internal air pressure of the inflation cone is inflated to a preset pressure difference, the internal pressure difference and the external pressure difference of the inflation cone are monitored by the air pressure sensor, and when the internal air pressure of the inflation cone is reduced to the preset pressure difference, the normally closed electromagnetic valve is opened again to perform secondary inflation.
The parachute device selects a ring sail parachute, and ejects and opens the parachute by adopting an ejector, so as to carry out secondary deceleration on the aircraft structure and enhance the damage resistance of the aircraft structure.
The connecting and separating mechanism comprises a bracket component, a spring actuator, separating nuts and bolts, wherein the aircraft structure is connected with an external space station through four separating nuts, bolts and bending moment loads caused by axial tension and compression and shearing force born by the bracket component, and when the aircraft structure is released, the four separating nuts are detonated to unlock the nuts and the bolts, and after the unlocking, the spring actuator pushes the aircraft structure to move and separate from the bracket component to separate from the space station.
The control cabin is used for carrying out energy supply and full flight stage control on the aircraft structure, realizing circuit connection of all parts of the aircraft structure and matching with the electrical performance requirement of the aircraft structure, carrying out orbit control on the aircraft structure by matching the orbit control cabin with the orbit control engine, and arranging a star sensor, a navigation module, an optical fiber inertial navigation module and matched equipment in the orbit control cabin.
After the aircraft structure is separated from the space station, carrying out rail changing braking through a gesture rail control cabin, carrying out self-adjusting gesture and off-rail braking to enter a return rail, casting the gesture rail control cabin after the return gesture is established, and completing first inflation and deployment before the flexible inflation cone enters the atmosphere at a preset rail height;
the aircraft structure enters an inflation unfolding state from a folding and folding state, enters an atmospheric layer in an inflation unfolding configuration and enters a deceleration process, and after the aircraft structure descends to a designated height, carries out secondary inflation, and enters a return process;
the parachute device is deployed and landed safely within the specified speed range.
A full-speed domain multiple deceleration descending control method of a flexible umbrella cone assembly comprises the following steps:
the downstream aircraft structure is separated from the external space station;
performing rail-changing braking, and performing self-attitude-adjusting and off-rail braking on the structure of the downlink aircraft;
after the returning gesture is established, the gesture throwing rail control cabin enters a returning rail;
starting to inflate at a preset track height, and completing the first inflation and deployment of the flexible inflation cone before entering the atmosphere;
the descending aircraft structure enters the atmosphere in an inflated and expanded pneumatic configuration and then enters the atmosphere for deceleration, and the descending aircraft structure is inflated for the second time after descending to the dense atmosphere;
the parachute device is deployed and landed safely within the specified speed range.
After the flexible inflatable cone is inflated for the second time, the internal absolute pressure is not less than the atmospheric pressure during landing;
the parachute device is deployed at the end of the return process and safely landed at a landing speed of not more than 13 m/s.
Compared with the prior art, the invention has the advantages that:
(1) The full-speed-domain multiple deceleration descending system and the control method of the flexible parachute cone assembly provided by the invention are based on the space product descending system of the inflatable reentry deceleration technology and the traditional parachute deceleration technology, integrate three functional modules of reentry heat prevention, deceleration stabilization and landing buffering, simplify the whole reentry and return working process, have light weight, small occupied space, can greatly save the emission cost, and have the advantages of flexibility and economy. Is expected to become one of the main technical approaches of reentry and deceleration of the future spacecraft;
(2) The invention can realize the repeated return of the space station effective load, satisfies the timely and batched return of the space station effective load, forcefully promotes the long-term operation capability of the space station in China, and provides a brand new technical approach for the descending of the space station effective load. The goods descending rule of the space station in China is enlarged, so that international cooperation projects and business application projects are driven, and the international influence and economic value of the space station in China are improved;
(3) The space product descending system based on the flexible inflatable reentry and deceleration technology combines the multiple stable deceleration of the parachute deceleration technology mode, simultaneously returns the effective load of the space station in the multiple stable deceleration of the parachute deceleration technology mode to the working flow in a descending mode, provides a stable descending system structure layout form, and solves the problem of lacking a descending system design scheme capable of meeting the high-frequency and low-cost descending of a large amount of effective loads of the space station through the on-orbit mass center inertia automatic balancing scheme design of the descending system.
Drawings
FIG. 1 is a schematic diagram of a downlink system return operation process provided by the invention;
FIG. 2 is a schematic diagram of a structural layout of a folded and collapsed state of the down going aircraft provided by the invention;
FIG. 3 is a schematic illustration of the inflated deployment of the down going vehicle of the present invention;
fig. 4 is a schematic view of opening and closing a load cabin door of a downlink aircraft provided by the invention;
FIG. 5 is a schematic diagram of an automatic mass inertia balancing mechanism provided by the invention;
FIG. 6 is a schematic view of the structure of the inflatable cone provided by the invention;
FIG. 7 is a schematic illustration of a thermal protective skin structure provided by the invention;
FIG. 8 is a schematic view of a connection and disconnection mechanism provided by the invention;
FIG. 9 is a flow chart of a downstream implementation of the space station payload provided by the invention;
Detailed Description
A flexible parachute cone assembly full-speed domain multiple deceleration descending system and a control method thereof are provided, wherein the descending system comprises an aircraft structure, a flexible inflatable cone, a connecting and separating structure and a parachute device, the descending system is arranged on a ship along with a freight aircraft in a furled state, a descending load is placed in a load cabin of the descending system on the orbit by a spaceman, the descending system is installed on an outer hanging point of the space station cabin or a docking channel cabin door of the space station through a space station mechanical arm or the spaceman, and the descending system is separated from the space station at a certain speed through an ejection and separation device. After a certain safety distance is reached, the descending system carries out track-changing braking, then self-adjusts the gesture and carries out track-leaving braking, a gesture-throwing track control cabin is built after a returning gesture is built, and the track-throwing track control cabin enters a returning track in a preset reentry gesture. The descending system is inflated and unfolded into an inverted cone shape before entering the atmosphere, and is decelerated, stably descends and inflated for the second time after entering the atmosphere, so that pneumatic heating and overload in the reentry process are born. The last return section adopts parachute to further reduce the speed to realize safe landing, the speed is equivalent to the landing speed of the return satellite, and the safety of effective load can be ensured.
In the descending system, the aircraft structure comprises a rigid nose cone, a control cabin, a load cabin and a gesture track control cabin, wherein the rigid nose cone is arranged at the head of the aircraft structure and is used for bearing the standing point temperature and the standing point pressure in the reentry descending process of the aircraft structure, the flexible inflation cone is arranged at one side of the rigid nose cone, which is close to the tail of the aircraft structure, and is used for bearing the aerodynamic force and the thermal load in the return process of the aircraft structure so as to realize pneumatic deceleration, the control cabin is arranged at one side of the flexible inflation cone, which is close to the tail of the aircraft structure, and is used for carrying out energy supply and full flight stage control on the aircraft structure, the load cabin is used for carrying out centroid adjustment balancing of the aircraft structure and is arranged at one side of the control cabin, which is close to the tail of the aircraft structure, and the gesture track control cabin is arranged at the tail of the aircraft structure and is matched with the control cabin to carry out gesture control and off-track braking on the aircraft structure and maintain the stable gesture of the aircraft structure; the connection and disconnection structure is used for connecting the aircraft structure with the external space station; the parachute device is arranged at the axial center position of the load cabin before opening the parachute, so that recovery and deceleration of the aircraft structure after opening the parachute are realized;
the remote measuring and marking device is arranged in the control cabin and is used for realizing measurement and control and marking of the whole working stage of the aircraft structure and carrying out data feedback;
the rigid nose cone is of a rigid heat-proof structure, the edge of the rigid nose cone is connected with the minimum ring bag body of the inflation system of the flexible inflation cone through a pressing strip, the load cabin is used for mounting a payload, the load cabin is subjected to descending packaging loading through an opening of the side wall, the side wall is divided into three parts, one part is a fixed cabin wall which is not movable or rotates, the other two parts are rotatable cabin doors which rotate around cabin door shafts respectively, when the rotatable cabin doors are closed, the cabin doors can be automatically locked, the cabin doors are closed, when the rotatable cabin doors are opened, the rotatable cabin doors are opened by pulling a pull pin, a cable special channel is arranged in the center of the load cabin, and the cable arrangement requirement of all cabin sections is provided for the aircraft structure;
the load cabin is used for adjusting and balancing the mass center of the system after loading the load through the mass center inertia automatic balancing mechanism, and the mass center inertia automatic balancing mechanism is installed through the control cabin; the flexible inflatable cone comprises an inflatable cone body, a thermal protection skin and a packaging structure, wherein the inflatable cone body is formed by stacking and intersecting circular rings after being unfolded, the circular rings are communicated with each other, the thermal protection skin consists of an ablation-resistant layer, a heat insulation layer and a bearing layer, and the ablation-resistant layer is made of a high-temperature-resistant fiber fabric and a heat-resistant coating and is used for bearing external airflow scouring and pneumatic heat flow; the heat insulation layer blocks heat from being transferred to the inside, and the temperature of the internal air-blocking bearing layer and the temperature of the return cabin structure are protected to be in a usable range; the bearing layer is made of a bearing fabric film-coated material and is used for preventing external high-temperature gas from flowing into the structure through the gaps, and the bearing fabric is used for bearing and transmitting pneumatic load on the surface of the structure;
the flexible inflation cone is internally provided with an inflation assembly, the inflation assembly is installed through a control cabin and comprises a high-pressure gas cylinder, a normally closed electric explosion valve, a normally closed electromagnetic valve and an air pressure sensor, when the flexible inflation cone is unfolded, an external sealing rope is cut off, the normally closed electromagnetic valve and the normally closed electric explosion valve are opened to inflate the inflation cone, the inflation cone drives a thermal protection skin to be unfolded in place and provides pretightening force for the thermal protection skin, when the air pressure in the inflation cone is inflated to a preset pressure difference, the normally closed electromagnetic valve is closed, the pressure difference between the inside and the outside of the inflation cone is monitored by the air pressure sensor, and when the air pressure in the inflation cone is reduced to a preset pressure difference, the normally closed electromagnetic valve is opened again to perform secondary inflation;
the parachute device selects a ring sail parachute, and the catapult is adopted to catapult and open the parachute, so that secondary deceleration is carried out on the aircraft structure, and the damage resistance of the aircraft structure is enhanced;
the connecting and separating mechanism comprises a bracket component, a spring actuator cylinder, separating nuts and bolts, wherein the aircraft structure is connected with an external space station through four separating nuts, bolts and bending moment loads caused by axial tension and compression and shearing force born by the bracket component, and when the aircraft structure is released, the four separating nuts are detonated to unlock the nuts and the bolts, and after the unlocking, the spring actuator cylinder pushes the aircraft structure to move and separate from the bracket component so as to separate from the space station;
the control cabin is used for carrying out energy supply and full flight stage control on the aircraft structure, realizing circuit connection of all parts of the aircraft structure and matching with the electrical performance requirement of the aircraft structure, wherein the attitude and orbit control cabin is used for carrying out orbit control on the aircraft structure by matching with the control cabin through an orbit control engine, and a star sensor, a navigation module, an optical fiber inertial navigation module and matched equipment are arranged in the attitude and orbit control cabin;
after the aircraft structure is separated from the space station, carrying out rail changing braking through a gesture rail control cabin, carrying out self-main gesture adjustment and off-rail braking, building a gesture-throwing rail control cabin after returning to the gesture, entering a return track in a preset gesture, and starting to inflate the flexible inflation cone at the preset track height, so as to complete the first inflation and deployment before entering the atmosphere;
the aircraft structure enters an inflation unfolding state from a folding and folding state, enters an atmospheric layer in an inflation unfolding configuration and enters a deceleration process, and after the aircraft structure descends to a designated height, carries out secondary inflation, and enters a return process;
the parachute device is deployed and landed safely within the specified speed range.
The following further description of the preferred embodiments is provided in connection with the accompanying drawings of the specification:
in the current embodiment, the working procedure of the downlink system is as shown in fig. 1:
the downstream aircraft structure is separated from the external space station;
performing rail-changing braking, and controlling a downlink aircraft structure, a downlink aircraft structure and a gesture rail;
establishing a return gesture, entering a return process, and throwing a gesture rail control cabin;
starting to inflate at a preset track height, and completing the first inflation and deployment of the flexible inflation cone before entering the atmosphere;
the descending aircraft structure enters the atmosphere in an inflated and expanded pneumatic configuration and then enters the atmosphere for deceleration, and the descending aircraft structure is inflated for the second time after descending to the dense atmosphere;
the parachute device at the tail end of the return flow is unfolded and safely landed in a specified speed range, so that the downlink system is ensured to safely land at a landing speed of not more than 13 m/landing speed.
The whole structure of the down going aircraft, namely the down going system, is folded and locked as shown in figure 2.
The rigid nose cone is of a rigid heat-proof structure and bears standing point temperature and standing point pressure in the reentry and descending process of the aircraft, and the edge of the nose cone is connected with the minimum ring bag body of the inflation system through the pressing strip. The load compartment is used for installing the payload, and can provide a cargo installation space of not less than 180L. The load cabin carries out descending package loading through the side wall opening, the whole side wall is divided into three parts, one part of the load cabin is fixed with the cabin wall and is not movable or rotates, the other two parts of the load cabin are rotatable cabin doors which rotate around cabin door shafts respectively, the two cabin doors can be automatically locked when being folded, the cabin doors are closed, and when the cabin doors are required to be opened, the cabin doors can be opened only by pulling the pull pins, as shown in fig. 4. In addition, a cable special channel is arranged in the center of the load cabin, so that the cable arrangement requirements of the upper cabin section and the lower cabin section are met. The control pod may be used to install power supplies, inflation assemblies, control devices, automatic mass inertia balancing mechanisms, telemetry indexing devices, etc., as shown in fig. 5. The mass center inertia automatic balancing mechanism is used for adjusting and balancing the mass center of the system after loading the load.
The flexible inflatable cone has the function of realizing the pneumatic deceleration function of the descending system and can bear aerodynamic force and thermal load in the returning process. The flexible inflatable cone comprises an inflatable cone body, a thermal protection skin and a packaging structure, and the structural form is shown in fig. 6. After the inflatable cone is unfolded, as shown in fig. 3, the inflatable cone is in a half cone angle of 60 degrees and is formed by stacking and intersecting a plurality of circular rings, and the circular rings are communicated with each other. The thermal protection skin and each circular ring of the inflatable cone are connected and fixed in a flexible connection mode, and the thermal protection skin consists of an ablation-resistant layer, a heat insulation layer and a bearing layer, as shown in fig. 7. The ablation-resistant layer is made of a high-temperature-resistant fiber fabric and a heat-resistant coating and is mainly used for bearing external airflow scouring and pneumatic heat flow and protecting the internal structure from being damaged; the heat insulation layer is used for blocking heat from being transferred to the inside, absorbing most of heat, and protecting the temperature of the internal air blocking bearing layer and the temperature of the return cabin structure from being in a usable range; the bearing layer is made of a bearing fabric film-coated material and is used for preventing external high-temperature gas from flowing into the structure through the gaps, protecting the heat-proof system and the return cabin structure, and meanwhile, the bearing fabric is used for bearing and transmitting pneumatic loads on the surface of the structure. The inflation assembly consists of a high-pressure gas cylinder, a normally-closed electric explosion valve, a normally-closed electromagnetic valve and a gas pressure sensor. When the inflation cone is unfolded, the outer sealing rope of the inflation cone is cut off, and the normally closed electromagnetic valve and the normally closed electric explosion valve are opened simultaneously to inflate the inflation cone in two ways, so that the inflation cone drives the thermal protection skin to be unfolded in place and provides pretightening force for the thermal protection skin. When the pressure difference inside the inflatable cone reaches a preset pressure difference, the electromagnetic valve is closed, and the pressure difference inside and outside the inflatable cone is monitored by using the air pressure sensor. When the system descends to a certain height, the electromagnetic valve is opened again to carry out secondary inflation.
The parachute device mainly decelerates the descending system and selects the ring sail parachute. The ring sail umbrella has reliable opening, small opening load and strong damage resistance, and is widely used for recovery of spacecrafts. The parachute adopts a mode of catapulting and opening the parachute by a catapult.
The connection and separation mechanism is used for realizing the functions of installation, fixation and ejection separation of a downlink system and a space station. The connection and separation mechanism mainly comprises a bracket component, a spring actuator cylinder, a separation nut and other components, as shown in fig. 8. When in connection, the four separating nut-bolt-brackets bear bending moment load caused by axial tension and compression and shearing force, the force transmission path is simple, and the bracket component is uniformly stressed. And when the release is carried out, the four separation nuts are detonated, so that the separation nut-bolt unlocking is realized. After unlocking, the switching ring is separated from the bracket, and the spring actuator cylinder pushes the descending system to move, so that the switching ring is separated from the space station. The scheme has the advantages of simple structure, small separation impact, high separation reliability and the like.
The control device mainly realizes the energy supply of the downlink system and the control function of the full working stage. The comprehensive controller can complete the control of the return re-entry process of the downlink system after being separated from the space station, realizes the circuit connection among all electric products, and meets the electric performance test requirements of the ground and the space. The attitude and orbit control device mainly realizes the attitude control and off-orbit braking functions of a downlink system, realizes the attitude control of stable system attitude, maneuvering and system screwing, attitude adjustment and the like through an attitude control engine, and realizes the orbit control of the system through the orbit control engine. The attitude and orbit control device comprises a star sensor, a navigation module, an optical fiber inertial navigation module and matched software.
The remote measurement positioning device mainly realizes the measurement and control and positioning functions of the downlink system in the whole working stage, the navigation communication integrated machine not only sends relevant remote measurement signals back to the ground, but also comprises a Beidou module, and the positioning of the system is realized by using a Beidou positioning technology and a short message communication technology.
In the implementation, the space product descending system based on the inflatable reentry and deceleration technology and the traditional parachute and deceleration technology integrates three functional modules of reentry and heat prevention, deceleration stabilization and landing buffering, simplifies the whole reentry and return working process, has light weight, small occupied space, can greatly save the emission cost, and has the advantages of flexibility and economy. Is expected to become one of the main technical approaches of future spacecraft reentry (entry) and deceleration. The system can realize the repeated return of the space effective load, meet the timely and batched return of the effective load of the space station, forcefully promote the long-term operation capability of the space station in China, and provide a brand new technical approach for the descending of the effective load of the space station. The goods descending rule of the space station in China is enlarged, the international cooperation project and the business application project are driven, and the international influence and the economic value of the space station in China are improved.
The flow of the space station payload downstream in the embodiment is as shown in fig. 9:
(1) Transmitting rail
And placing the descending system in the folded state on a cargo grid of a cargo ship shelf, launching the ascending cargo ship along with the cargo ship through a carrier rocket, and then crossing and docking the cargo ship with a space station after the cargo ship is in orbit.
(2) Load loading
When the payload needs to descend, the payload is loaded into the payload bay of the descending system by the astronaut. After loading, the mass center inertia automatic balancing mechanism automatically balances the mass center inertia of the system according to the loaded state of the load, and compensates the system deviation after loading the load.
(3) Evacuation of
The preparation of the relevant electrical interface and the on-orbit electrical performance test before the downstream system is evacuated are completed, the downstream system can be installed on an external hanging point of a space station cabin or a docking passage cabin door of the space station through an astronaut or a mechanical arm, and the downstream system is ejected through a connecting and separating mechanism, so that the downstream system is evacuated from the space station.
(4) Off-track
And after the descending system is separated from the space station, the system is powered on, and after autonomous attitude and orbit control and off-orbit braking are completed, the attitude and orbit control cabin is separated.
(5) Inflatable deployment
After the attitude and orbit control cabin is separated, the inflation and deployment of the inflation cone are completed before the descending system is reentered the atmosphere.
(6) Reentry deceleration
The downlink system reenters the atmosphere at the designated reentry point, and the telemetry indexing device is powered up to continuously download the position information to the ground. According to the real-time data of the return trajectory, when the system descends to a preset height in the dense atmosphere, the control system starts the air charging cone to perform secondary air charging, so that the internal pressure meets the requirement of being in an overpressure state after landing.
(7) Parachute speed reducer
And returning to the tail section, when the descending system falls to a lower height, ejecting the parachute cabin cover, unfolding the parachute, and utilizing the parachute to implement final deceleration on the descending system, so that the steady descending speed of the descending system is reduced to not more than 13m/s, and the safety of effective load is ensured.
(8) Landing standby
And after landing, continuously transmitting a position signal through a position marking device in the navigation communication integrated machine for searching by ground searching staff after landing.
The invention provides a space product descending system based on a flexible inflatable reentry and deceleration technology and combining a parachute deceleration technology mode, and a space station effective load descending return workflow of multiple stable deceleration. The method simplifies the whole reentry and recovery working process, has light weight and small occupied space, and can greatly save the transmitting cost. The technology can also be applied to the fields of space personnel emergency return, deep space exploration, space debris mitigation, hypersonic aircraft deceleration and the like.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.
What is not described in detail in the present specification belongs to the known technology of those skilled in the art.
Claims (11)
1. A flexible umbrella cone assembly full-speed domain multiple deceleration descending system is characterized in that:
the device comprises an aircraft structure, a flexible inflatable cone, a connecting and separating structure and a parachute device, wherein the aircraft structure comprises a rigid nose cone, a control cabin, a load cabin and a gesture rail control cabin, the rigid nose cone is arranged at the head of the aircraft structure and is used for bearing standing point temperature and standing point pressure in the reentry process of the aircraft structure, the flexible inflatable cone is arranged at one side of the rigid nose cone, which is close to the tail of the aircraft structure, and is used for bearing aerodynamic force and thermal load in the return process of the aircraft structure so as to realize pneumatic deceleration, the control cabin is arranged at one side of the rigid nose cone, which is close to the tail of the aircraft structure, and is used for carrying out energy supply and full flight stage control on the aircraft structure, the load cabin is used for carrying out centroid adjustment balancing on the aircraft structure and is arranged at one side of the control cabin, which is close to the tail of the aircraft structure, and the gesture rail control cabin is arranged at the tail of the aircraft structure, and the gesture rail control cabin is matched with the control cabin to carry out gesture control and off-track braking on the aircraft structure and maintain the stable gesture of the aircraft structure; the connection and disconnection structure is used for connecting the aircraft structure with the external space station; the parachute device is arranged at the axial center position of the load cabin before opening the parachute, and recovery and deceleration of the aircraft structure after opening the parachute are realized.
2. A flexible cone assembly full speed domain multiple deceleration descending system according to claim 1, wherein:
the remote measuring and marking device is arranged in the control cabin and is used for realizing measurement and control and marking of the whole working stage of the aircraft structure and carrying out data feedback.
3. A flexible cone assembly full speed domain multiple deceleration descending system according to claim 2, wherein:
the rigid nose cone is of a rigid heat-proof structure, the edge of the rigid nose cone is connected with the minimum ring bag body of the inflation system of the flexible inflation cone through a pressing strip, the load cabin is used for installing a payload, the load cabin is subjected to descending packaging loading through a side wall opening, the side wall is divided into three parts, one part is a fixed cabin wall which is not movable or rotates, the other two parts are rotatable cabin doors which rotate around cabin door shafts respectively, when the rotatable cabin doors are closed, the cabin doors can be automatically locked, the cabin doors are closed, when the rotatable cabin doors are opened, the rotatable cabin doors are opened by pulling a pull pin, a cable special channel is arranged in the center of the load cabin, and the cable arrangement requirement of all cabin sections is provided for the aircraft structure.
4. A flexible cone assembly full speed domain multiple deceleration descending system according to claim 3, wherein:
the load cabin is used for adjusting and balancing the mass center of the system after loading the load through the mass center inertia automatic balancing mechanism, and the mass center inertia automatic balancing mechanism is installed through the control cabin; the flexible inflatable cone comprises an inflatable cone body, a thermal protection skin and a packaging structure, wherein the inflatable cone body is formed by stacking and intersecting circular rings after being unfolded, the circular rings are communicated with each other, the thermal protection skin consists of an ablation-resistant layer, a heat insulation layer and a bearing layer, and the ablation-resistant layer is made of a high-temperature-resistant fiber fabric and a heat-resistant coating and is used for bearing external airflow scouring and pneumatic heat flow; the heat insulation layer blocks heat from being transferred to the inside, and the temperature of the internal air-blocking bearing layer and the temperature of the return cabin structure are protected to be in a usable range; the bearing layer is made of a bearing fabric film-coated material and is used for preventing external high-temperature gas from flowing into the structure through the gaps, and the bearing fabric is used for bearing and transmitting pneumatic load on the surface of the structure.
5. The flexible cone-umbrella assembly full-speed domain multiple-speed-reduction downlink system according to claim 4, wherein:
the flexible inflation cone is internally provided with an inflation assembly, the inflation assembly is installed through a control cabin and comprises a high-pressure gas cylinder, a normally closed electric explosion valve, a normally closed electromagnetic valve and an air pressure sensor, when the flexible inflation cone is unfolded, an external sealing rope is cut off, the normally closed electromagnetic valve and the normally closed electric explosion valve are opened to inflate the inflation cone, the inflation cone drives a thermal protection skin to be unfolded in place and provides pretightening force for the thermal protection skin, the normally closed electromagnetic valve is closed when the internal air pressure of the inflation cone is inflated to a preset pressure difference, the internal pressure difference and the external pressure difference of the inflation cone are monitored by the air pressure sensor, and when the internal air pressure of the inflation cone is reduced to the preset pressure difference, the normally closed electromagnetic valve is opened again to perform secondary inflation.
6. The flexible cone-umbrella assembly full-speed domain multiple-speed-reducing downlink system according to claim 5, wherein:
the parachute device selects a ring sail parachute, and ejects and opens the parachute by adopting an ejector, so as to carry out secondary deceleration on the aircraft structure and enhance the damage resistance of the aircraft structure.
7. The flexible cone-umbrella assembly full-speed domain multiple-speed-reduction downlink system according to claim 6, wherein:
the connecting and separating mechanism comprises a bracket component, a spring actuator, separating nuts and bolts, wherein the aircraft structure is connected with an external space station through four separating nuts, bolts and bending moment loads caused by axial tension and compression and shearing force born by the bracket component, and when the aircraft structure is released, the four separating nuts are detonated to unlock the nuts and the bolts, and after the unlocking, the spring actuator pushes the aircraft structure to move and separate from the bracket component to separate from the space station.
8. The flexible cone-umbrella assembly full-speed domain multiple-speed-reduction downlink system according to claim 7, wherein:
the control cabin is used for carrying out energy supply and full flight stage control on the aircraft structure, realizing circuit connection of all parts of the aircraft structure and matching with the electrical performance requirement of the aircraft structure, carrying out orbit control on the aircraft structure by matching the orbit control cabin with the orbit control engine, and arranging a star sensor, a navigation module, an optical fiber inertial navigation module and matched equipment in the orbit control cabin.
9. The flexible cone-umbrella assembly full-speed domain multiple-speed-reduction downlink system according to claim 8, wherein:
after the aircraft structure is separated from the space station, carrying out rail changing braking through a gesture rail control cabin, carrying out self-adjusting gesture and off-rail braking to enter a return rail, casting the gesture rail control cabin after the return gesture is established, and completing first inflation and deployment before the flexible inflation cone enters the atmosphere at a preset rail height;
the aircraft structure enters an inflation unfolding state from a folding and folding state, enters an atmospheric layer in an inflation unfolding configuration and enters a deceleration process, and after the aircraft structure descends to a designated height, carries out secondary inflation, and enters a return process;
the parachute device is deployed and landed safely within the specified speed range.
10. A method for controlling full-speed domain multiple deceleration downlink of a flexible umbrella cone assembly implemented by a downlink system according to claim 9, comprising:
the downstream aircraft structure is separated from the external space station;
performing rail-changing braking, and performing self-attitude-adjusting and off-rail braking on the structure of the downlink aircraft;
after the returning gesture is established, the gesture throwing rail control cabin enters a returning rail;
starting to inflate at a preset track height, and completing the first inflation and deployment of the flexible inflation cone before entering the atmosphere;
the descending aircraft structure enters the atmosphere in an inflated and expanded pneumatic configuration and then enters the atmosphere for deceleration, and the descending aircraft structure is inflated for the second time after descending to the dense atmosphere;
the parachute device is deployed and landed safely within the specified speed range.
11. The method for controlling full-speed domain multiple deceleration downlink of the flexible umbrella cone assembly according to claim 10, wherein the method comprises the following steps:
after the flexible inflatable cone is inflated for the second time, the internal absolute pressure is not less than the atmospheric pressure during landing;
the parachute device is deployed at the end of the return process and safely landed at a landing speed of not more than 13 m/s.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310190662.9A CN116142491A (en) | 2023-02-24 | 2023-02-24 | Full-speed-domain multiple deceleration descending system of flexible umbrella cone assembly and control method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310190662.9A CN116142491A (en) | 2023-02-24 | 2023-02-24 | Full-speed-domain multiple deceleration descending system of flexible umbrella cone assembly and control method |
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| CN116142491A true CN116142491A (en) | 2023-05-23 |
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|---|---|---|---|
| CN202310190662.9A Pending CN116142491A (en) | 2023-02-24 | 2023-02-24 | Full-speed-domain multiple deceleration descending system of flexible umbrella cone assembly and control method |
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| Country | Link |
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| CN (1) | CN116142491A (en) |
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- 2023-02-24 CN CN202310190662.9A patent/CN116142491A/en active Pending
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