CN109737826B

CN109737826B - Sub-level structure

Info

Publication number: CN109737826B
Application number: CN201910140761.XA
Authority: CN
Inventors: 请求不公布姓名
Original assignee: Beijing Star Glory Space Technology Co Ltd
Current assignee: Beijing Star Glory Space Technology Co Ltd
Priority date: 2019-02-25
Filing date: 2019-02-25
Publication date: 2024-03-08
Anticipated expiration: 2039-02-25
Also published as: CN109737826A

Abstract

The invention discloses a sub-level structure which comprises an arrow body, a pneumatic speed reducing mechanism and a pneumatic anti-collision mechanism. The pneumatic speed reducing mechanism comprises a pneumatic head and an ablation preventing layer, the pneumatic head is a second air bag which can be folded and unfolded, and the second air bag is covered outside the head of the arrow body; the pneumatic anti-collision mechanism is provided with a first airbag which can be folded and unfolded, and the first airbag is covered outside the tail part of the rocket body. The second air bag is in a symmetrical structure after being inflated, and has good pneumatic stability. An ablation prevention layer is arranged on the outer wall of the second air bag, so that the second air bag cannot be burnt when flying in high altitude and high temperature, and the second air bag can decelerate an arrow body in high altitude and high temperature; the second air bag has foldability, so that the space and weight occupied by the second air bag on the arrow body are reduced; meanwhile, the first air bag can flexibly buffer the tail part of the rocket body when the tail part of the rocket body lands, so that the rocket body is prevented from being damaged.

Description

Sub-level structure

Technical Field

The invention relates to the technical field of spaceflight of solid carrier rockets, in particular to a sub-level structure.

Background

In the process of returning different trajectory, the sub-level structure of the solid carrier rocket is separated from the upper pole structure, and then the sub-level structure can continuously rise to the outside of the atmosphere to fly for a period of time under the action of inertia, and then returns to the atmosphere of the earth, so that the solid carrier rocket is landed on the ground. The existing sub-level structure mainly comprises an arrow body, a front section structure arranged at the head of the arrow body and a rear section structure arranged at the rear section of the arrow body. The front section structure mainly comprises a speed reducer, a navigation guidance and control system, a gesture control system and other devices. When the sub-level structure returns to the earth atmosphere to land downwards, the friction resistance between the deceleration device and the external air is increased, so that the flying speed of the sub-level structure is reduced, and the sub-level structure is landed on the ground safely.

Because the sub-level structure flies at a high speed in the high air entering the atmosphere, the rocket body rubs with the atmosphere to generate a large amount of heat, the heat enables the environment where the rocket body is positioned to be a high-temperature environment, the speed reducer is easy to burn at a high temperature, the speed reducer is required to have a certain ablation resistance, but the existing parachute cannot resist the high temperature, and is easy to burn in the high-temperature environment; when the sub-level structure descends to a low altitude, particularly when the sub-level structure is landed on the ground, the speed reducing device is required to have a certain flexible buffer function so as to prevent the speed reducing device from directly and rigidly striking the ground to damage an arrow body. In addition, be convenient for retrieve the arrow body, still need reduction gear to be better in the pneumatic stability of deceleration in-process, otherwise the position randomness after the arrow body lands is too big, is inconvenient for retrieving the arrow body.

In order to meet the above-mentioned requirement for a speed reducer, the speed reducer in the prior art is generally provided with a speed reducer for decelerating the arrow body at a high temperature and a parachute for decelerating and landing the arrow body at a low altitude. The reducer is provided with a rigid heat-resistant large blunt end, and the diameter of the large blunt end is gradually increased along the axial direction of the reducer from the head part to the tail part and is in a symmetrical structure so as to increase the resistance of the large blunt end and the flying stability; meanwhile, the big blunt tip is made of rigid and high-temperature resistant materials, so that the rigid speed reducer can reduce the speed of the arrow body in a high-altitude high-temperature environment, when the arrow body descends to a low altitude, the parachute is unfolded and sleeved on the big blunt tip and the head of the arrow body, the parachute plays a buffering role in landing of the arrow body, and the installation landing of the arrow body is realized.

In order to enable the speed reducer to have the required pneumatic stability, ablation resistance and landing buffer performance in the speed reducer speed reducing process, the speed reducer with the rigid heat-resistant large blunt tip and the parachute are required to be arranged independently, however, the two types of speed reducers are combined, so that the whole speed reducer is complex in structure; especially, the rigid heat-proof speed-reducing head can not be folded and stored, and the occupied space is large, so that the weight borne by the sub-level structure is large, and the cost required by arrow body recovery is high.

Meanwhile, when the sub-level structure is landed, the head part of the arrow body of the sub-level structure is landed firstly, and the tail part of the arrow body of the sub-level structure is landed, but no protective structure is arranged on the tail part of the existing sub-level structure, and the arrow body is directly impacted on the ground to generate impact force so as to damage the arrow body.

Disclosure of Invention

Therefore, the technical problem to be solved by the invention is that the existing sub-level structure has complex structure and heavy weight and the landing tail of the rocket body is easy to be knocked.

To this end, the invention provides a sub-level structure comprising

An arrow body;

the pneumatic anti-collision mechanism is arranged on the arrow body and provided with an inflatable first air bag which can be changed between a furled state and a deployed state;

the pneumatic speed reducing mechanism is arranged on the arrow body and comprises

A pneumatic head, which is an inflatable second airbag that can be changed between a folded state and an unfolded state; the second air bag is in a revolving body shape in the unfolding state, and the diameter of the second air bag is gradually increased along the axial direction of the second air bag from the windward side of the second air bag to the leeward side of the second air bag;

at least one ablation-preventing layer arranged on the outer wall surface of the second air bag;

the first air bag and the second air bag are suitable for being respectively covered outside the tail part and the head part of the arrow body when in an unfolding state.

Optionally, in the above sub-level structure, the pneumatic speed reducing mechanism further includes at least one heat insulating layer disposed between the second air bag outer wall surface and the ablation preventing layer.

Optionally, in the above sub-level structure, the second air bag includes a head and a reverse taper provided on a distal end of the head, and a generatrix of the head is a smooth curve.

Optionally, in the above sub-level structure, the head is spherical.

Optionally, in the above sub-level structure, the second air bag and/or the first air bag include at least two branch air bags connected end to end in turn along the circumferential direction thereof;

the two adjacent branch air bags are sealed and separated, and each branch air bag is provided with an inflation inlet.

Optionally, in the sub-level structure, any two adjacent branch air bags are sealed and separated by flexible ribs arranged in the first air bag or the second air bag where the two branch air bags are respectively arranged; or alternatively

At least one flexible rib is arranged in any one of the air bags; or at least one flexible rib is arranged in the first air bag or the second air bag, and the flexible rib spans all the branch air bags along the circumferential direction of the air bags where the flexible rib is positioned.

Optionally, in the sub-level structure, at least one flexible rib is arranged in any one of the air bags; or at least one flexible rib is arranged in the first air bag or the second air bag, and when the flexible ribs span all the air bags along the circumferential direction of the air bags where the flexible ribs are respectively positioned, the number of the flexible ribs is at least two, and all the flexible ribs are arranged on the corresponding air bags in a stacking manner along the axial direction of the air bags where the flexible ribs are respectively positioned.

Optionally, in the above sub-level structure, the first air bag and/or the second air bag are/is fixed on the arrow body through a rigid connecting piece embedded in a concave area surrounded by the leeward surfaces of the first air bag and/or the second air bag;

the second bladder or first bladder is adapted to house the respective rigid connector.

Optionally, in the above sub-level structure, the rigid connection member is telescopically arranged on the arrow body along the axial direction of the respective air bag by a telescopic assembly.

Optionally, in the above sub-level structure, the first air bag is in a shape of a revolution body in the deployed state, and the diameter of the first air bag is gradually increased along the axial direction from the windward side of the first air bag toward the leeward side of the first air bag.

The technical scheme of the invention has the following advantages:

1. the invention provides a sub-level structure, which comprises a pneumatic speed reducing mechanism and a pneumatic anti-collision mechanism, wherein the pneumatic speed reducing mechanism comprises a pneumatic head and at least one ablation-preventing layer, and the pneumatic head is an inflatable second air bag which can be changed between a furled state and an unfolded state; the second air bag is in a revolving body shape and is suitable for being covered outside the head of the arrow body when in the unfolding state; the diameter of the second air bag in the unfolding state is gradually increased along the axial direction from the windward side of the second air bag to the leeward side of the second air bag, so that the second air bag is axisymmetric after being inflated, and has good pneumatic stability in the flying process; the ablation-preventing layer is arranged on the outer wall surface of the second air bag, and can absorb a large amount of heat during vaporization besides the heat insulation performance of the ablation-preventing layer so as to reduce the temperature of the environment where the air bag is positioned, even if the ablation-preventing layer is burnt out, the ablation-preventing layer can take away a certain amount of heat, and reduce the temperature of the environment where the air bag is positioned, so that the second air bag cannot be burnt out when flying in high altitude and high temperature, and the second air bag can decelerate an arrow body in the high altitude and high temperature; and play the cushioning effect to the arrow body when low altitude landing, the second gasbag can be in the furling state before not inflating, reduces the space and the weight that the second gasbag occupy on the arrow body. That is, only one pneumatic speed reducing mechanism is arranged on the head of the arrow body, and the pneumatic speed reducing device starts to reduce the speed of the arrow body from the moment that the arrow body just enters the atmosphere until the arrow body lands on the ground, so that the structure of the existing speed reducing device is simplified; meanwhile, the pneumatic anti-collision mechanism can be changed between a furled state and an unfolding state, the first air bag is covered outside the tail of the arrow body in the unfolding state, and when the tail of the arrow body lands, the first air bag plays a role in protecting the arrow body due to the buffering effect of the first air bag, so that the arrow body is prevented from being damaged.

2. The sub-level structure provided by the invention further comprises at least one heat insulation layer arranged between the outer wall surface of the second air bag and the ablation-preventing layer, and a plurality of heat insulation layers are arranged, so that the high temperature resistance of the second air bag in a high-altitude high-temperature environment is further improved, and the second air bag can be decelerated in the high-temperature environment even if ablation is prevented from being burnt.

3. The invention provides a sub-level structure, wherein a second air bag comprises a head part and an inverted cone arranged at the tail end of the head part; the bus of the head is a smooth curve; the shape and pneumatic stability of the pneumatic head are improved.

4. The sub-level mechanism provided by the invention comprises at least two branch air bags which are sequentially connected end to end along the circumferential direction of the first air bag and/or the second air bag; adjacent two the branch air bags seal and separate, every be equipped with the inflation inlet on the branch air bag, a plurality of branch air bags mutually independent, even the sealing of some branch air bags is poor, also can not influence the gas tightness of other branch air bags, further improves the gas tightness of first gasbag or second gasbag, prolongs its life.

5. The sub-level structure provided by the invention further comprises the flexible ribs, the flexible ribs limit the appearance of the second air bag or the first air bag, and the external impact acting force of the air bag is enhanced, so that the pneumatic head has stable structure and higher strength, simultaneously keeps good pneumatic appearance, and further improves the pneumatic stability or the anti-collision property of the air bag.

6. According to the sub-level structure provided by the invention, the pneumatic head is fixed on the arrow body through the rigid connecting piece embedded in the concave area; the concave area of the second air bag is suitable for covering the heads of the rigid connecting piece and the arrow body, and the second air bag plays a role in heat protection on the heads of the rigid connecting piece and the arrow body in a high-temperature and high-altitude environment, so that the heads of the rigid connecting piece and the arrow body are not in direct contact with the outside at high temperature.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic diagram of a sub-level structure provided in embodiment 1 of the present invention;

FIG. 2 is a partial schematic view of the sub-level structure provided in embodiment 1 of the present invention;

FIG. 3 is a schematic diagram showing the structure of the pneumatic reduction mechanism according to the embodiment 1 of the present invention in the front view;

FIG. 4 is a schematic view of a pneumatic head of the pneumatic reduction mechanism of FIG. 3;

FIG. 5 is a schematic side view of the pneumatic head of the pneumatic reduction mechanism of FIG. 3;

FIG. 6 is a schematic partial cross-sectional view of the pneumatic head of the pneumatic reduction mechanism of FIG. 3;

FIG. 7 is a schematic side view of the telescoping rod, rigid connection and arrow in the pneumatic reduction mechanism of the neutron level structure of FIG. 2;

FIG. 8 is a schematic view of the telescopic rod of FIG. 6;

reference numerals illustrate:

1-a pneumatic head; 11-head; 12-reverse taper; 13-ballonets; 14-flexible ribs;

2-a rigid connection;

31-a heat insulation layer; 32-an ablation-preventing layer;

41-a first lever; 42-a second lever; 43-elastic locking member;

5-umbrella bag;

6-arrow body;

7-a first balloon.

Detailed Description

The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.

In addition, the technical features of the different embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.

Example 1

The present embodiment provides a sub-level structure, as shown in fig. 1 to 8, including an arrow body, a pneumatic speed reducing mechanism provided on the head of the arrow body, and a pneumatic anti-collision mechanism provided on the tail of the arrow body. The pneumatic speed reducing mechanism comprises a pneumatic head 1, a plurality of layers of heat insulation layers 31, an anti-ablation layer 32 and a rigid connecting piece 2.

Specifically, the air head 1 is an inflatable second airbag that is convertible between a collapsed state and an expanded state; the second air bag is in a revolving body shape when in an unfolding state, and the diameter of the second air bag is gradually increased along the axial direction of the second air bag from the windward side of the second air bag to the leeward side of the second air bag; the lee surface of the second air bag surrounds a concave area, and when the second air bag is in a unfolding state, the concave area is covered outside the head of the arrow body. Specifically, as shown in fig. 3 and 4, the second balloon includes a head 11 and an inverted cone 12 provided on the end of the head 11, the head 11 is in the shape of a spherical cap, and the diameter of the second balloon is gradually increased from the head toward the inverted cone along the axial direction thereof, so that the second balloon has a large blunt end in a symmetrical structure, a large resistance coefficient and good running stability.

As shown in fig. 4, when inflated, in the projection view of the vertical plane (the plane where the Y axis and the Z axis are located) of the air head 1, the inverted cone 12 is in an inverted trapezoid shape, and the edges where the two waists of the inverted trapezoid are located are tangential and transition with the end of the head 11, so that the appearance of the air head 1 is in a streamline shape with smooth transition, and the second air bag better meets the requirements of the aerodynamic deceleration appearance and the aerodynamic stability.

The lee surface of the second air bag surrounds a concave area, the second air bag is fixed on the arrow body through a rigid connecting piece 2 embedded in the concave area, and the rigid connecting piece 2 is cylindrical and made of a high-temperature-resistant rigid material, such as a high-temperature-resistant stainless steel tube. As shown in fig. 2, one end of the rigid connection member 2 is fixed on the head of the arrow body 6, the other end is sequentially and hermetically penetrated on the leeward side and the windward side of the head 11 of the second air bag, and the axis of the rigid connection member 2 coincides with the axis of the pneumatic head 1, so that the pneumatic head 1 is symmetrically distributed on the rigid connection member 2, and the rigid connection member 2 plays a supporting and fixing role on the second air bag, so that the leeward side of the second air bag is limited by the rigid connection member 2 under the action of external air, and the second air bag further can maintain a symmetrical external structure, thereby further improving the pneumatic stability of the second air bag.

As shown in fig. 2, the reverse taper 12 covers the rigid connection member 2 and the head of the arrow body, or the reverse taper 12 covers the head and the middle of the arrow body, a plurality of heat insulation layers and ablation prevention layers (mentioned below) are arranged on the outer wall surface of the second air bag, and the second air bag covers the rigid connection member, so that the second air bag plays a role in heat protection on the rigid connection member 2, and the rigid connection member 2 is prevented from being directly contacted with the external high-temperature environment.

In order to make the pneumatic head 1 have better pneumatic stability, the position of the pneumatic head when landing is convenient to be in a controllable range, an adjusting component (not shown in the figure) is further arranged on the arrow body 6, and the posture of the second air bag in the unfolding state is adjusted, so that the second air bag is in a symmetrical structure.

The adjustment assembly corresponds to a Reaction Control System (RCS) or a gesture control system. For example, the adjusting assembly includes a gas supply mechanism and a plurality of gas nozzles, for example, the gas supply mechanism is a high-pressure gas cylinder provided on the arrow body 6, and the high-pressure gas cylinder stores high-pressure gas. The air ejector tubes are arranged and fixed on the bulkhead of the rocket body and are positioned in the inner cavity of the rocket body and are connected with the air outlet pipeline of the high-pressure air cylinder, the nozzles of the air ejector tubes are used for ejecting high-pressure air to the openings on the bulkhead, and after the high-pressure air is ejected out of the openings, reaction force is generated on the bulkhead to drive the rocket body to move, so that the movement of the air bag fixed on the rocket body is changed, and the air bag spreading posture is adjusted. The air outlet pipe of the high-pressure air bottle is provided with a valve, and the air inlet close to the air jet pipe is provided with a flow control valve, so that the air jet pipe can conveniently adjust the driving force of the bulkhead, and the flow control valve is an electromagnetic valve or a stop valve.

In addition, the pneumatic head 1 may be made of nylon or other flexible materials, such as carbon fiber. Meanwhile, the spray pipe is arranged in the inner cavity of the rigid connecting piece 2, so that the speed reducing device is compact in structure.

As shown in fig. 2, a plurality of heat insulation layers 31 are provided on the outer wall surface of the air head 1, for example, three heat insulation layers 31 are provided, and the three heat insulation layers 31 are respectively made of metal foil, carbon cloth and ceramic fiber, or aramid fiber, aramid fiber and woven ceramic fabric. Or the three heat insulation layers 31 are all metal foils, and the three heat insulation layers 31 are all ceramic fibers or ceramic fabrics and the like. For example, the ceramic fiber may be composed of alumina, silica, diboron trioxide or the like in a desired ratio, and the ratio may be not limited as long as the ceramic fiber can be prepared. The material of the heat insulating layer can also be other existing high-temperature resistant materials.

Alternatively, the heat insulating layer 31 may be two layers, one layer, four layers, five layers, etc., and the specific number of layers is according to actual requirements. The more the number of layers of the heat insulating layer 31 is, the more the heat protecting effect on the air head 1 is. Optionally, the heat insulation layers 31 are fixed with the outer wall surface of the pneumatic head 1 through adhesive bonding, and the heat insulation layers 31 of two adjacent layers are also fixed through adhesive bonding. Or the heat insulation layer 31 with the required thickness is directly formed on the outer wall surface of the pneumatic head 1 by adopting other modes, such as spraying, and after the heat insulation layer 31 of the previous layer is solidified, the heat insulation layer 31 of the next layer is coated.

As shown in fig. 3, at least one ablation preventing layer 32 is disposed on the outer wall surface of the outermost insulating layer 31, for example, one or two or more ablation preventing layers 32 are disposed, and the ablation preventing layers 32 may be made of epoxy resin materials. Optionally, the anti-ablation layer 32 is coated on the heat insulation layer 31, and after the pneumatic speed reducing mechanism is used for a period of time, if part of the anti-ablation layer is burnt out, the anti-ablation layer can be coated on the burnt-out position, so that the anti-ablation layer of the second air bag has repairability, and the second air bag can be reused. As a variant, other high molecular polymers or fibers may be used for the ablation preventing layer 32. Such as carbon fibers, or carbon nanotube fibers, etc.

The ablation-preventing layer 32 plays a role in preventing ablation of the pneumatic head 1, so that the second air bag can slow down the arrow body in a high-altitude high-temperature environment; meanwhile, the multi-layer heat insulation layer 31 further enhances the heat insulation function between the second air bag and the external high temperature environment, so that the heat in the external environment cannot directly act on the second air bag; even if the ablation-preventing layer 32 is burnt out, the multi-layer heat-insulating layer can still insulate the second air bag, so that the temperature of the second air bag is far lower than the burning temperature of the second air bag, and the pneumatic speed reducing mechanism has a required heat protection function, and can reduce the speed of the arrow body 6 from the high altitude and high temperature just entering the atmosphere until the second air bag safely lands. In addition, since the outer periphery of the rigid connection member 2 is surrounded by the second air bag, when the air head 1 decelerates in the high-altitude high-temperature environment, the ablation preventing layer 32 and the heat insulating layer 31 on the second air bag also play a role in heat protection of the rigid connection member 2.

For the second air bag, as shown in fig. 4, the second air bag comprises a plurality of air bags 13 which are connected end to end in turn along the circumferential direction, two adjacent air bags 13 are sealed and separated, and each air bag 13 is provided with an inflation inlet.

For example, the windward side and the leeward side of the second air bag are respectively formed by a first flexible plate and a second flexible plate which are in a whole, and then the first flexible plate and the second flexible plate are woven or sewed and fixed together in a similar manner to sewing, and a plurality of air bags 13 which are mutually sealed and isolated are formed along the circumferential direction. That is, the "fixing slits" of the adjacent two airbags 13 fix and seal the two airbags 13 apart.

Each air bag 13 is provided with an air charging port, each air charging port is connected with an air charging device through a first pipeline, and a one-way valve is arranged on the first pipeline to control whether the air charging device charges air into the air bags 13. For example, the inflator is a high-pressure air charge bottle provided on the arrow body 6. The plurality of branch air bags 13 are inflated independently, and even if one branch air bag 13 leaks, the air tightness of the other branch air bags 13 is not affected, and the speed reduction effect can be still achieved, so that the safety of the pneumatic speed reducer is increased. Optimally, the air charging port is arranged on the leeward surface of the lower second air bag, so that the air charging port is closer to a high-pressure air charging bottle arranged on the rocket body. In addition, the inflation ports at symmetrical positions need to be inflated simultaneously during inflation, ensuring that the second airbag also maintains a symmetrical profile during inflation.

To further improve the aerodynamic stability of the second balloon, a plurality of flexible ribs 14 are included within the second balloon. For example, the flexible ribs 14 are annular, the flexible ribs 14 penetrate through the second air bags along the circumferential direction of the second air bags, one annular flexible rib can span all the air bags 13, when a plurality of annular flexible ribs 14 are arranged, the flexible ribs 14 are arranged in a stacked mode in the axial direction of the second air bags, the supporting effect on the second air bags is achieved, the appearance of the inflated second air bags can be kept symmetrical, the external impact force can be borne, and the pneumatic stability is better.

Or, for another example, among all the flexible ribs 14, the flexible rib 14 has a ring shape, wherein the flexible rib 14 provided at the head 11 has a ring shape; the longitudinal section of the flexible rib 14 arranged on the inverted cone 12 is inverted trapezoid, and the longitudinal section of the inverted cone 12 is inverted trapezoid, so that the flexible rib 14 with the inverted trapezoid longitudinal section can be more matched with the structure of the inverted cone, and the flexible rib is arranged on the pneumatic head without changing the structure of the pneumatic head, and plays a supporting role. Or the flexible ribs 14 with different shapes can be independently arranged in one supporting air bag 13 to independently support each supporting air bag 13, so that the appearance of the air bag is further controllable, and the symmetrical structure and the pneumatic stability of the pneumatic head 1 can be maintained in the whole deceleration process.

Alternatively, the flexible ribs 14 are provided directly between the windward side and the leeward side of each airbag 13, and the shape of the flexible ribs is not limited as shown in fig. 5. For example, the flexible ribs may be cylindrical, or may be plate-shaped. The flexible ribs are generally formed by thin steel wires or other materials, and only have flexibility and certain rigidity to support the second air bag so that the second air bag keeps a symmetrical structure and can keep symmetry under external impact force. The arrangement of the flexible ribs enhances the ground impact resistance of the second air bag, so that the pneumatic stability of the whole second air bag is high, and the second air bag has a good pneumatic appearance.

Alternatively, the above-mentioned "fixing slits" between the adjacent two air bags 13 are connected by a flexible rib seal, and the flexible rib is not provided in each air bag, and the second air bag can be supported and the strength thereof can be enhanced.

The second air bag is mainly changed between a furled state and an unfolded state through an inflating device, the inflating device can be a high-pressure air bottle fixed on the rocket body 6, and an air outlet of the high-pressure air bottle is connected with an inflating port; or the inflating device comprises a high-pressure inflating bottle and a compressor, the inflating device is used for inflating the branch air bag 13 under the cooperation of the high-pressure inflating bottle and the compressor, the high-pressure inflating bottle is used for inflating the branch air bag 13 before the sub-level structure enters the atmosphere, the compressor is used for inflating after the sub-level structure enters the atmosphere, or the compressor is used for inflating the high-pressure inflating bottle, and the high-pressure inflating bottle is still used for inflating the branch air bag 13, so that the second air bag is switched from a furled state to an unfolding state; conversely, when the gas in the second air bag needs to be exhausted, the gas in the second air bag can be reversely pumped back into the high-pressure gas cylinder, or the second air bag is provided with an exhaust port, so that the gas in the second air bag is exhausted, the second air bag is switched from the unfolding state to the gathering state, and the exhaust port is correspondingly provided with a detachable sealing cover.

The telescopic assembly is arranged on the arrow body 6 in a telescopic way through the rigid connecting piece 2, and as shown in fig. 7 and 8, the telescopic assembly comprises a plurality of telescopic rods which are uniformly distributed along the circumference of the rigid connecting piece 2, one end of each telescopic rod is connected with the rigid connecting piece 2, and the other end of each telescopic rod is connected with the head of the arrow body 6.

For each telescopic rod, as shown in fig. 8, each telescopic rod includes a first rod 41, a second rod 42 and an elastic locking member 43, and for convenience of illustration, both ends of the first rod 41 are respectively denoted as a first end and a second end, and both ends of the second rod 42 are respectively denoted as a third end and a fourth end. The first end of the first bar 41 is fixed to the rigid connection 2, for example in a hinged manner, the third end of the second bar 42 is sleeved on the second end of the first bar 41, and the fourth end of the second bar 42 is fixed to the arrow body 6, for example also in a hinged manner.

In the overlapping region where the first rod 41 and the second rod 42 are sleeved, a plurality of first openings 421 are formed in the side wall of the second rod 42 at intervals, and elastic locking members 43 are radially protruded from the outer wall surface of the first rod 41, for example, the elastic locking members 43 are elastic protrusions or plungers, when the first rod 41 is driven by a driving force (mentioned below), the first rod 41 moves away from the second rod 42, the elastic locking members 43 are compressed and slide in the second rod 42, when the first rod 41 is extended outwards to a position, the elastic locking members 43 are located at the position of one first opening 421, and the elastic locking members 43 are ejected into the first openings 421 by releasing the compression amount, so that the first rod 41 and the second rod 42 are locked.

Alternatively, in order to enhance the connection firmness of the first rod 41 and the second rod 42, a plurality of elastic locking members are arranged in the axial direction of the first rod 41, and when the first rod 41 slides in place, the elastic locking members are ejected into the first holes in a one-to-one correspondence manner; alternatively, a plurality of elastic locking members may be disposed in the circumferential direction of the first rod 41, and a plurality of first openings may be disposed in the circumferential direction of the second rod 42, thereby enhancing the connection firmness of the first rod 41 and the second rod 42.

In addition, the pneumatic speed reducing mechanism further comprises an umbrella bag 5, the umbrella bag 5 is fixed on the head of the arrow body 6 through an explosion bolt before the second air bag is not inflated, a cabin is arranged on the head of the arrow body generally, a containing cavity is formed between the cabin and the umbrella bag, and the second air bag after being folded is arranged in the umbrella bag 5. When the second air bag is required to be unfolded, the explosion bolt is exploded firstly, the locking force between the umbrella bag and the front end of the rocket body is relieved by the explosion bolt, then the high-pressure gas is released by the high-pressure gas cylinder on the rocket body, the high-pressure gas drives the umbrella bag to be separated from the front end of the rocket body, or the umbrella bag is pulled by arranging a small rocket, so that the umbrella bag is separated from the front end of the rocket body 6, the umbrella bag 5 is connected with the second air bag through a pulling component, for example, the pulling component is flexible high-temperature-resistant steel wire, when the umbrella bag 5 extends far away from the rocket body 6, a driving force is applied to the second air bag, the second air bag and the rigid connecting piece 2 are driven to be pulled out from the head of the rocket body 6, and the rigid connecting piece 2 simultaneously drives the first rod 41 to extend outwards, so that the telescopic rod is in an extending state; the respective airbags 13 are inflated with gas by the corresponding inflator, so that the second airbag is switched from the initial state of being folded and stored in the bag 5 to the deployed state. Alternatively, the umbrella bag may be replaced with a high pressure sleeve.

The pneumatic crash-proof mechanism has an inflatable first air-bag 7 adapted to be housed on the tail of the arrow body 6 and being convertible between a stowed condition and a deployed condition, i.e. a recessed area defined by the leeward side of the first air-bag 7, the first air-bag 7 being adapted to be housed outside the tail of the arrow body in the deployed condition. In this embodiment, the first balloon 7 has the same structure as the second balloon, except that: because the first air bag 7 plays a role in buffering when the arrow body lands and is not in a high-temperature environment, the outer wall surface of the first air bag 7 does not need to be provided with a heat insulation layer and an ablation prevention layer, other structures are the same as those of the second air bag, the first air bag 7 is connected with the arrow body through a rigid connecting piece and a telescopic component, the arrow body is also provided with the adjusting component for adjusting the posture of the first air bag 7, and related contents refer to the description contents of the second air bag and are not repeated. Optimally, the first balloon 7 and the second balloon are symmetrically arranged on the arrow body.

The sub-level structure of this embodiment, first, set up insulating layer 31 and anti-ablation layer 32 on the outer wall of the second gasbag, because anti-ablation layer besides its thermal insulation performance, because it can absorb a large amount of heat while vaporizing, in order to reduce the temperature of the environment where the second gasbag is located, even if anti-ablation layer burns off, it can take away certain heat too, reduce the temperature of the environment where the second gasbag is located, make the second gasbag can use in the high altitude high temperature environment, the second gasbag will not burn off, the second gasbag can slow down the arrow body 6; secondly, the second air bag is arranged as a symmetrical large blunt point, and flexible ribs 14 are arranged in the second air bag, so that the second air bag has strong external impact resistance and pneumatic stability, and the landing position of the second air bag is in a controllable range; then, before the second air bag is not used, the second air bag is in a folded state and is contained in the umbrella bag 5, so that the weight and occupied volume of the speed reducer are reduced, and the structure is compact; in the whole process that the arrow body 6 returns to the atmosphere and lands on the ground, only one pneumatic speed reducing mechanism is required to be arranged to finish high altitude Wen Jiansu and buffer landing; due to the pneumatic anti-collision structure, the tail of the arrow body is buffered after the first air bag 7 is inflated when the arrow body is landed, so that the tail of the arrow body can directly collide on the ground, the tail of the arrow body is prevented from being damaged, and the sub-level structure realizes the integrated arrangement of flexibility, foldability, thermal protection, high temperature resistance, pneumatic stability and tail landing anti-collision of the pneumatic speed reducer.

As a first alternative embodiment of example 1, the adjusting component may be replaced by another structure, for example, the adjusting component includes a first magnetic layer disposed between the outer wall surface of the second air bag and the heat insulation layer 31, and is made of a permanent magnet material, and a second magnetic body disposed on the arrow body 6, and the second magnetic body is made of a soft magnetic material, and is energized with an alternating current, so that the second magnetic body generates a polarity, for example, a positive direction is energized, one end of the second magnetic body facing the first magnetic layer is S-pole, a reverse direction is energized, and the polarity of the second magnetic body facing the first magnetic layer is N-pole, so that the second magnetic body generates an outward repulsive force or an adsorption force to the second air bag, thereby adjusting the deployment posture of the second air bag. In the practical use process, an attitude detector, such as a camera, for acquiring the attitude of the second air bag according to photographing is further arranged in the second air bag flying process, and as a further deformation, the adjusting component is not required to be arranged.

As a second alternative embodiment of example 1, there may be other numbers of telescopic rods in the telescopic assembly, such as one, two, three, four, etc., where one telescopic rod is provided, the first end of the first rod of the telescopic rod is directly fixed to the end of the rigid connection member 2; when the telescopic rods are arranged, the telescopic rods are arranged on the periphery of the rigid connecting piece 2, so that the telescopic action of the rigid connecting piece 2 on the rigid connecting piece 2 is larger when the rigid connecting piece 2 is telescopic relative to the arrow body 6, and the posture of the second air bag is kept in a required symmetrical state; the telescopic rod may also be replaced by an elastic member, such as a spring. The two ends of the spring are respectively connected with the rigid connecting piece 2 and the arrow body 6, or as deformation, a telescopic component is not required to be arranged.

As a third alternative of example 1, the flexible ribs 14 may also be omitted, in which case the second bladder relies mainly on its own profile symmetry and the action of the high pressure gas, so that the second bladder remains aerodynamically stable.

As a fourth alternative embodiment of example 1, the second air bag may be a whole, and the plurality of air bags 13 are not provided, and the air inlets may be symmetrically provided on the second air bag, so that two high-pressure air cylinders are used to inflate the second air bag at the same time, thereby ensuring the symmetry of the second air bag.

As a fifth alternative embodiment of example 1, the head 11 may not be in the shape of a spherical cap, for example, the head 11 may be in the shape of a bullet; or, the pneumatic head 1 is a revolution body, the diameter of the second air bag is gradually increased from the windward side to the leeward side along the axial direction, and the second air bag can be in a symmetrical structure in the unfolding state of the second air bag, so that the second air bag can maintain good pneumatic stability. Similarly, the structure of the first air bag is similar to that of the second air bag, and will not be described herein again, please refer to the structure of the second air bag, but the outer wall surface of the first air bag does not need to be provided with the heat insulation layer and the ablation prevention layer.

As a sixth alternative embodiment of example 1, the heat insulating layer may be omitted and only ablation prevention may be provided.

Example 2

The present embodiment provides a sub-level structure differing from the sub-level structure provided in embodiment 1 only in that: the structure of the first air bag is different, and the pneumatic anti-collision mechanism in this embodiment can also be used for other air bags, such as a U-shaped air bag, an S-shaped air bag, a V-shaped air bag or other air bags, and the air bags can be covered on the tail part of the arrow body, so that the tail part of the arrow body can be prevented from being directly impacted with the ground when the arrow body lands.

It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the invention.

Claims

1. A sub-level structure, characterized by comprising

An arrow body (6);

a pneumatic anti-collision mechanism arranged on the arrow body and provided with an inflatable first air bag (7) which can be changed between a furled state and an unfolded state;

the inflating device is arranged on the arrow body (6);

a pneumatic speed reducing mechanism arranged on the arrow body (6) and comprising

A pneumatic head (1) which is an inflatable second airbag that can be changed between a folded state and an unfolded state; the second air bag is in a revolving body shape in the unfolding state, and the diameter of the second air bag is gradually increased along the axial direction of the second air bag from the windward side of the second air bag to the leeward side of the second air bag;

at least one ablation preventing layer (32) arranged on the outer wall surface of the second air bag;

the first air bag (7) and the second air bag are suitable for being respectively covered outside the tail part and the head part of the arrow body (6) when in an unfolding state;

the second air bag and/or the first air bag (7) comprises at least two branch air bags (13) which are sequentially connected end to end along the circumferential direction, wherein the two adjacent branch air bags (13) are sealed and separated, an inflation inlet is arranged on each branch air bag (13), and the inflation inlet is communicated with the inflation device;

any two adjacent branch air bags (13) are sealed and separated by flexible ribs (14) arranged in the first air bag (7) or the second air bag where the branch air bags are respectively positioned; or, flexible ribs (14) are arranged in any one of the air bags (13); or, flexible ribs (14) are arranged in the first air bag or the second air bag, and the flexible ribs (14) span all the branch air bags (13) along the circumferential direction of the air bags where the flexible ribs are respectively positioned;

flexible ribs (14) are arranged in any one of the air bags (13); or, flexible ribs (14) are arranged in the first air bag or the second air bag, when the flexible ribs (14) span all the branch air bags (13) along the circumferential direction of the air bags where the flexible ribs (14) are respectively located, at least two flexible ribs (14) are arranged, and all the flexible ribs (14) are arranged on the corresponding air bags in a stacked mode along the axial direction of the air bags where the flexible ribs are respectively located.

2. The sub-level structure according to claim 1, characterized in that the pneumatic reduction mechanism further comprises at least one thermal insulation layer (31) arranged between the second balloon outer wall surface and the ablation preventing layer (32).

3. The sub-level structure according to claim 1 or 2, characterized in that the second balloon comprises a head (11) and a reverse taper (12) provided on the end of the head (11), the generatrix of the head (11) being a smooth curve.

4. A sub-level structure according to claim 3, characterized in that the head (11) is spherical in shape.

5. The sub-level structure according to any one of claims 1-2, 4, characterized in that the first (7) and/or second (2) air-bag are fixed to the arrow body (6) by means of rigid connectors (2) embedded in recessed areas defined by the respective leeward surfaces;

the second or first balloon (7) is adapted to cover the respective rigid connection (2).

6. A sub-structure according to claim 5, characterized in that the rigid connection (2) is telescopically arranged on the arrow body (6) by means of a telescopic assembly in the axial direction of the respective balloon.

7. The sub-structure according to any one of claims 1-2, 4, 6, wherein the first balloon (7) is in the form of a body of revolution in the deployed state and the diameter of the first balloon (7) increases gradually in its axial direction from the windward side of the first balloon towards the leeward side of the first balloon.