CN113280694B - Integrated air bag speed reduction device for interstage separation of aircraft and design method - Google Patents
Integrated air bag speed reduction device for interstage separation of aircraft and design method Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
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Abstract
The invention provides an integrated air bag speed reducer for interstage separation of an aircraft and a design method, the integrated air bag speed reducer comprises a gas generator, an integrated air bag, a fixed supporting structure, a heat-proof dimensional cover and a control device, wherein the control device is connected with the gas generator, sends out a working signal of the gas generator, and starts to work; the fixed supporting structure is an annular groove fixed on a tail cabin under the aircraft; the gas generator is fixed on the fixed supporting structure, the gas outlet of the gas generator is connected with the gas inlet of the integrated air bag, the integrated air bag is fixed on one side of the fixed supporting structure close to the shell of the guided missile, and the heat-proof dimensional cover covers the integrated air bag and is fixed on the shell of the aircraft in the front and back direction along the axis direction of the guided missile. The invention reduces the complexity of the system, does not generate forward flame and forward flying objects during working, and avoids the adverse effect on the safety of a measurement and control system and a structure of an upper-level aircraft caused by the generation of the forward flame and the forward flying objects.
Description
Technical Field
The invention belongs to the technical field of overall design of aircrafts, and particularly relates to an integrated airbag speed reduction device for interstage separation of an aircraft and a design method.
Background
The glide vehicle in the near space adopts a configuration that solid rocket boosting stages are connected in series with a high-lift-drag ratio upper stage, the glide vehicle is quickly accelerated after launching and takes off, the track is sufficiently pressed down to reduce the probability of finding, and the glide vehicle flies in the near space at a high speed after the upper stage is separated from the boosting stages. Compare traditional ballistic aircraft, promoted range ability and penetration ability by a wide margin, had huge development potential, military strong countries such as the United states, russia continue to promote near space gliding aircraft's military application through projects such as "HTV-2", "pioneer".
Because the near space glider track is low in height, the interstage separation points are generally distributed in the height range of 20-60 km, in order to ensure that the attitude of the separation process in the atmosphere of the glider is controllable, the separation time is generally selected at the moment when the thrust of the lower stage engine initially enters the tailing section, at the moment, although the engine charge is exhausted, the lower forward residual thrust can still be generated under the aftereffect action of a combustion chamber, for the interstage separation of the glider in the height range of 20-60 km, because the difference between the upper stage resistance and the lower stage resistance is generally small, after two-stage mechanical unlocking, the lower stage pneumatic resistance is not enough to quickly pull open the two-stage relative distance, and the lower stage possibly has the tendency of following the upper stage under the action of the aftereffect thrust.
In order to fully ensure the separation safety, a method of arranging a group of thrust terminating devices or a group of separation impulse devices at the following stages is generally adopted for solving the problems:
1) And a thrust terminating device. A group of controllable hole opening mechanisms are arranged on a front seal head of the engine, the engine is started before and after interstage separation unlocking, and the residual pressure of a combustion chamber of the engine is rapidly discharged through holes of the front seal head. The mode has the defects that the diversion channels corresponding to the number of the holes are required to be arranged on the upper-level connection cabin and the lower-level connection cabin, so that the effective space in the connection cabins is greatly occupied, the optimization of equipment layout is influenced, and the diversion mechanism is complex in connection matching and poor in reliability. In addition, when the thrust termination device works, forward-direction flying objects such as forward-direction flame, blocking sheets (covers) and the like are generated, and adverse effects are generated on the measurement and control system and the structural safety of the upper-level aircraft.
2) And (4) a separating impulse device. By providing a certain separation thrust reversal amount in the separation process, the forward residual thrust of the rocket engine is counteracted, the lower stage is decelerated, and the separation safety is ensured. The traditional separation impulse device generally adopts a reverse-thrust rocket, and the mode has the defects that the reverse-thrust rocket has larger structural mass and reduces the total effective load capacity, and the reverse-thrust rockets are usually arranged in groups, occupy the space in an aircraft cabin and influence the optimized layout of equipment. In addition, when the impulse separating device works, forward-direction flying objects such as forward-direction flame, a blocking sheet (cover) and the like are generated, and adverse effects are generated on the upper-level aircraft measuring and controlling system and the structure safety.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides an integrated airbag speed reduction device for interstage separation of an aircraft and a design method. The scheme of the invention can solve the problems in the prior art.
The technical scheme of the invention is as follows:
according to a first aspect, the integrated airbag speed reduction device for the interstage separation of the aircraft comprises a gas generator, an integrated airbag, a fixed supporting structure, a heat-proof dimensional cover and a control device, wherein the integrated airbag speed reduction device is positioned at the lower stage of the aircraft, the control device is connected with the gas generator, and when the aircraft sends out an interstage separation signal, the control device sends out a gas generator working signal to start working of the gas generator; the fixed supporting structure is an annular groove fixed on a lower-stage tail cabin of the aircraft; gas generator be fixed in fixed bearing structure on, its gas outlet links to each other with the air inlet of integral type gasbag, during the gas filling integral type gasbag that will produce, the integral type gasbag be fixed in one side that fixed bearing structure is close to the guided missile shell, be in fold condition when not aerifing, heat-proof dimension shape lid cover on the integral type gasbag to on being fixed in the aircraft shell around the axis direction of guided missile, being backed up when the integral type gasbag expandes, then backward movement under the incoming flow effect.
Furthermore, after the integrated air bag is inflated and expanded, the windward surface of the integrated air bag is in a concentric ring shape and is fixedly connected with the lower-stage body under the action of the fixed supporting structure.
Further, the diameter of the integrated air bag after being inflated and deployed is determined by the following formula:
the size of the S integrated airbag is the same as that of the D integrated airbag, the size of the D integrated airbag is the same as that of the D integrated airbag after the D integrated airbag is inflated and unfolded, and the D integrated airbag is the diameter of the lower windward section of the aircraft, wherein the determination formula of the S is as follows: f = Q · S ≧ P * F is the pneumatic resistance increased when the integrated air bag is completely unfolded, Q is the dynamic pressure of the upper and lower separation points of the aircraft, P * The residual thrust of the engine of the lower aircraft after the aircraft is separated.
Furthermore, the skirt-shaped mounting structure arranged outside the integrated air bag is matched with a compression ring matched with the skirt-shaped mounting structure in the fixed supporting structure, so that the integrated air bag is fixedly connected with the fixed supporting structure.
Further, the configuration number and the effective gas output quantity of the gas generators are selected according to the nominal filling volume of the air bag by the gas generators.
Furthermore, the fixed supporting structure is provided with a through hole at the part where the air inlet of the integrated air bag is connected with the air outlet of the gas generator, and an inflation pipe orifice structure is arranged to hermetically butt the air inlet of the integrated air bag and the air outlet of the gas generator, so that the situation that the air leakage does not occur in the inflating process of the integrated air bag is ensured.
Furthermore, the heat-proof dimensional cover is composed of n cover plates, the cover plates are formed by thin-wall light metal, the outer surfaces of the cover plates are coated with the heat-proof layers, the cover plates are installed in a lap joint mode along the circumferential direction to realize dimensional shape, and the cover plates are fixed with the installation openings at the upper edges of the grooves in a lap joint mode through dovetail-shaped lugs with half openings reserved in the front and the back.
According to a second aspect, there is provided a method for designing an integrated airbag deceleration device for interstage separation of an aircraft, comprising the following steps:
calculating to obtain the deployment diameter and the nominal filling volume of the integrated airbag according to the flying height and speed of the aircraft at the separation moment, the residual thrust of the lower-stage engine and the diameter of the windward section of the lower stage;
determining the configuration quantity and the effective gas output quantity of the gas generators according to the nominal filling volume and the volume of a tail cabin of the lower stage of the aircraft;
determining the shape of the integrated airbag according to the deployment diameter of the integrated airbag;
determining the material of the integrated air bag according to the dynamic pressure and the atmospheric pressure at the separation moment of the aircraft;
determining a folding mode and an installation and fixing mode of the integrated air bag according to the shape and the material of the integrated air bag;
determining the number of inflation ports of the integrated air bag and the connection mode of the inflation ports and the air outlets of the gas generators according to the number of the gas generators;
determining the shape of the heat-proof dimensional cover, the number of cover plates and the installation mode of the cover plates according to the appearance of the lower level of the aircraft;
and determining the material and the surface treatment mode of the heat-proof dimensional cover according to the external temperature and strength requirements before the separation of the aircraft.
Compared with the prior art, the invention has the following beneficial effects:
(1) The invention has simple structure, obviously reduces the complexity of the system and improves the reliability of the system compared with the traditional method;
(2) The integrated air bag is in the folded state before being started, so that the occupied space in the cabin is greatly reduced compared with the traditional method, and the optimization of the space layout of equipment on an aircraft is facilitated;
(3) The integrated airbag speed reducer does not generate forward flame and forward flying objects when working, and avoids the adverse effect of the generation of the forward flame and the forward flying objects on the safety of a measurement and control system and a structure of an upper-level aircraft in the traditional method.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 is a schematic diagram illustrating an integrated airbag deceleration device for interstage separation of an aircraft according to an embodiment of the invention;
FIG. 2 illustrates a schematic view of a close-space gliding aircraft equipped with an integrated airbag deceleration device according to an embodiment of the invention;
FIG. 3 is a schematic view showing an installation structure of an integrated airbag, gas generator and fixing support groove according to an embodiment of the present invention;
FIG. 4 is a schematic diagram illustrating a structural constraint form of a heat-proof dimensional cover and a laminated installation structure thereof, provided by the embodiment of the invention;
FIG. 5 illustrates a schematic diagram of the activation of an integrated airbag deceleration device provided in accordance with an embodiment of the present invention;
FIG. 6 is a schematic diagram illustrating steps of a design method of an integrated airbag deceleration device for interstage separation of an aircraft, provided by the embodiment of the invention.
The figures contain the following reference numerals:
1. an upper aircraft stage; 2. a lower aircraft stage; 3. an integral air bag; 4. fixing the support structure; 5. a gas generator; 6. a heat-proof dimensional cover; 7. a tail compartment; 301. a skirt mounting structure; 302, an inflation tube orifice structure; 401. pressing a ring; 501. clamping a hoop; 502. an inflation inlet; 601. a heat resistant coating; 602. dovetail lugs; 603. pressing nail
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
According to a first aspect, as shown in fig. 1 and 2, the invention provides an integrated airbag deceleration device for interstage separation of an aircraft, which comprises a gas generator 5, an integrated airbag 3, a fixed supporting structure 4, a heat-proof dimensional cover 6 and a control device, wherein the integrated airbag deceleration device is positioned in a tail cabin 7 of a lower stage 2 of the aircraft, the control device is connected with the gas generator 5, and when the aircraft sends an interstage separation unlocking signal, the control device sends a gas generator 5 working signal, and the gas generator 5 starts to work; the gas generator 5 is fixed on the fixed supporting structure 4, the gas outlet of the gas generator is connected with the gas inlet of the integrated airbag 3, generated gas is filled into the integrated airbag 3, the integrated airbag 3 is located on one side, close to the missile shell, of the fixed supporting structure 4 and is in a folded state when not being inflated, the heat-proof dimensional cover 6 covers the integrated airbag 3, is fixed on the aircraft shell in the front and back direction along the axis direction of the missile, is ejected when the integrated airbag 3 is unfolded, and then moves backwards under the action of incoming flow.
Further in one embodiment, the integrated airbag deceleration device start signal and the interstage separation unlocking signal share the same command. After the aircraft sends out an interstage separation unlocking/airbag speed reduction device starting signal, the interstage separation initiating explosive device works to realize the mechanical unlocking of the upper stage and the lower stage; the gas generator 5 is operated after receiving the activation signal, generates gas to inflate the airbag, the airbag is rapidly expanded and unfolded, and the external thermal protection dimensional cover 6 is dispersed outwards under the expansion effect of the airbag and moves backwards under the effect of incoming flow, as shown in fig. 5.
Further, in one embodiment, as shown in fig. 5, after the integrated airbag 3 is inflated and deployed, the windward surface of the integrated airbag is in a concentric ring shape and is fixedly connected with the lower stage body under the action of the fixed supporting structure 4, so that the windward area of the lower stage is greatly increased, the pneumatic resistance is increased, the lower stage is continuously decelerated and is far away from the upper stage, and the safety of interstage separation is ensured.
Further, in one embodiment, the diameter of the integrated airbag 3 after inflation and deployment is determined by the formula:
the S-integrated airbag is used for increasing the windward area when being completely unfolded, the D-integrated airbag is used for expanding the diameter after being inflated, D is the diameter of the windward section of the next level 2 of the aircraft, and the determination formula of the S is as follows: f = Q · S ≧ P * F is the pneumatic resistance increased when the integrated air bag is completely unfolded, Q is the upper and lower separation point dynamic pressure of the aircraft, P * The residual thrust of the engine of the lower aircraft after the aircraft is separated.
Further, in an embodiment, the skirt-shaped mounting structure 301 disposed outside the integrated airbag 3 is matched with the pressing ring 401 in the fixed support structure 4, so as to fixedly connect the integrated airbag 3 with the fixed support structure 4, and in other embodiments, other fixing manners may be adopted.
Further in one embodiment, the gas generators 5 select the configuration number and the effective gas output amount of the gas generators 5 according to the nominal filling volume of the airbag and the volume of the tail cabin 7, so that the product of the number of the gas generators 5 multiplied by the effective gas storage amount of each gas generator is not less than the nominal filling volume of the airbag; in one embodiment, to maintain the stability of the missile, the gas generators 5 are more than one in number and are distributed uniformly on the circumference of the fixed support structure 4.
Further, in an embodiment, the fixed supporting structure 4 is provided with a through hole at a portion where the air inlet of the integrated airbag 3 is connected with the air outlet of the gas generator 5, and the inflating pipe orifice structure 302 is arranged to hermetically abut the air inlet of the integrated airbag 3 with the air outlet of the gas generator 5, so as to ensure that no air leakage occurs in the inflating process of the integrated airbag 3.
Further, in one embodiment, the integrated airbag 3 is formed by coating rubber on nylon fabric, in other embodiments, rubber is impregnated or coated on high-strength fiber fabric, and the fiber fabric can be made of nylon, polyamide, polyester and the like on the premise of meeting the environmental conditions of use and storage.
Further, in one embodiment, as shown in fig. 4, the heat-proof dimensional cover 6 is composed of n cover plates, the cover plates are formed by thin-wall light metal, the heat-proof layer is coated on the outer surface of the cover plates, the cover plates are installed in a lap joint mode along the circumferential direction to realize dimensional shape, and the cover plates are fixed through the lap joint of dovetail lugs 602 with front and rear reserved half holes and installation openings at the upper edge of the groove through press nails 603.
According to a second aspect, as shown in fig. 6, there is provided a design method of the integrated airbag deceleration device for the interstage separation of the aircraft, which comprises the following steps:
calculating to obtain the deployment diameter and the nominal filling volume of the integrated airbag 3 according to the flying height and speed of the aircraft at the separation moment, the residual thrust of a lower-level engine and the diameter of a lower-level windward section;
further in one embodiment, the steps of calculating the deployed diameter and nominal inflation volume of the integral bladder 3 are as follows:
s1.1, designing and determining the flying height H, the flying speed v and the engine residual thrust P at the stage separation moment according to the flying track * ；
S1.2, according to H, looking up a table to obtain the atmospheric density rho, and calculating the dynamic pressure of the separation point
S1.3, the increased windward area when the integrated air bag is completely unfolded is S, the correspondingly increased pneumatic resistance is F, and F =is adopted to ensure the separation safetyQ·S≥P * 。
S1.4, recording that the diameter of the lower windward section is D, the expansion diameter of the integrated air bag is D, and the expansion height of the integrated air bag is h according to the specification
Resolving to obtain D, and further obtaining
The integrated air bag is designed into a circular ring shape, so that the nominal filling volume of the air bag is easy to calculate
In a specific embodiment, the separation point height H =30km, the velocity v =1800m/s, the residual thrust P * =15kN, the diameter of the next stage d =1.4m; finding the atmospheric density rho =0.0184kg/m 3 Separating point dynamic pressure Q =29.8kPa, and solving the airbag unfolding diameter D =1.61m, the corresponding unfolding height h =0.105m and the nominal filling volume V =0.041m of the airbag 3 。
Secondly, determining the configuration quantity and the effective gas output quantity of the gas generators 5 according to the nominal filling volume and the volume of the tail cabin 7 of the lower stage 2 of the aircraft;
in one embodiment, the number of gas generators 5 and the effective gas output are selected by the gas generators 5 according to the nominal filling volume of the airbag and the volume of the tail compartment 7, so that the product of the number of gas generators 5 multiplied by the effective gas storage amount of each is not less than the nominal filling volume of the airbag; in one embodiment, to maintain the stability of the missile, the gas generators 5 are more than one in number and are distributed uniformly on the circumference of the fixed support structure 4.
Determining the shape of the integrated airbag 3 according to the deployment diameter of the integrated airbag 3;
in one embodiment, the integrated airbag 3 is concentrically annular in the windward side after being inflated and deployed.
Fourthly, determining the material of the integrated air bag 3 according to the dynamic pressure and the atmospheric pressure of the aircraft at the separation moment;
in one embodiment, the integrated airbag 3 is formed by coating rubber with nylon fabric, in other embodiments, the integrated airbag may be formed by impregnating rubber or coating high-strength fiber fabric, and the fiber fabric may be made of nylon, polyamide, polyester, etc. under the premise of meeting the environmental conditions of use and storage.
Fifthly, determining the folding mode and the installation and fixing mode of the integrated air bag 3 according to the shape and the material of the integrated air bag 3;
in one embodiment, the integrated airbag 3 is made of a flexible material, and the integrated airbag 3 can be folded like a fan;
in one embodiment, the fixed support structure 4 is designed to fix the integrated airbag 3, the fixed support structure 4 is installed on the inner wall of the tail cabin 7 of the lower stage 2 of the aircraft, the integrated airbag 3 is located on one side, close to the shell of the missile, fixed to the fixed support structure 4, and the integrated airbag 3 is fixedly connected with the fixed support structure 4 by matching with the skirt-shaped installation structure 301 arranged outside the integrated airbag 3 and the compression ring 401 matched with the fixed support structure 4.
Step six, determining the number of the inflation openings 502 of the integrated airbag 3 and the connection mode of the inflation openings 502 and the air outlets of the gas generators 5 according to the number of the gas generators 5;
in one embodiment, the cylinder section of the gas generator 5 is provided with a hoop 501 for auxiliary fixing and limiting, and a flange plate is arranged on the gas outlet end face of the gas generator 5 and is connected with a through hole of the fixed supporting structure 4 to be matched and pressed on the inflating pipe orifice structure 302, so that the topological closure of the gas generator 5-gas outlet-gas inlet-air bag is realized.
Seventhly, determining the shape of the heat-proof dimensional cover 6, the number of cover plates and the installation mode of the cover plates according to the shape of the lower level 2 of the aircraft;
in one embodiment, the overall outline of the cover plate is rectangular, four corners are rounded, the cover plates are installed in a lap joint mode along the circumferential direction to realize dimensional shape, the cover plates are fixed with the installation openings at the upper edges of the grooves in a lap joint mode through dovetail-shaped lugs with half openings reserved in the front and back (axial direction), when the gas generator 5 receives an instruction to work, gas is filled into the airbag through the spray pipe, when the airbag is expanded to a certain degree, the cover plate is deformed, constraint at the half openings is relieved, and the heat-proof dimensional cover 6 is dispersed backwards under the action of head-on high-speed airflow.
And step eight, determining the material and the surface treatment mode of the heat-proof dimensional cover 6 according to the external temperature and strength requirements before the separation of the aircraft.
In one embodiment, the heat-proof dimensional cover 6 is formed by thin-wall light metal, and the outer surface of the heat-proof dimensional cover is coated with a heat-proof layer, so that the requirements of heat protection and light weight are met.
In conclusion, compared with the prior art, the integrated airbag deceleration device with the interstage separation of the aircraft and the design method thereof provided by the invention have at least the following advantages:
(1) The invention has simple structure, obviously reduces the complexity of the system and improves the reliability of the system compared with the traditional method;
(2) The integrated air bag is in the folded state before being started, so that the occupied space in the cabin is greatly reduced compared with the traditional method, and the optimization of the space layout of equipment on an aircraft is realized;
(3) When the integrated airbag speed reducer works, forward flames and forward flying objects are not generated, so that adverse effects of the generation of the forward flames and the forward flying objects on the safety of a measurement and control system and a structure of an upper-level aircraft in the traditional method are avoided;
(4) The integrated air bag speed reducer has the advantages of simple structure, easy realization of a forming process, low engineering difficulty, low manufacturing cost and higher practical value.
For ease of description, spatially relative terms such as "over 8230 \ 8230;,"' over 8230;, \8230; upper surface "," above ", etc. may be used herein to describe the spatial relationship of one device or feature to another device or feature as shown in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary terms "at 8230; \8230; 'above" may include both orientations "at 8230; \8230;' above 8230; 'at 8230;' below 8230;" above ". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. An integrated airbag deceleration device for interstage separation of an aircraft, which is characterized by comprising a gas generator, an integrated airbag, a fixed supporting structure, a heat-proof dimensional cover and a control device, wherein the integrated airbag deceleration device is positioned at the lower stage of the aircraft, the control device is connected with the gas generator, and when the aircraft sends out an interstage separation signal, the control device sends out a gas generator working signal and the gas generator starts to work; the fixed supporting structure is an annular groove fixed on a lower-stage tail cabin of the aircraft; the integrated air bag is fixed on one side of the fixed supporting structure close to the shell of the missile and is in a folded state when not inflated, and after the integrated air bag is inflated and unfolded, the windward side of the integrated air bag is in a concentric ring shape and is fixedly connected with the lower-stage body under the action of the fixed supporting structure; the heat-proof dimensional cover is composed of n cover plates, the cover plates are formed by thin-wall light metal, heat-proof layers are coated on the outer surfaces of the cover plates, dimensional shapes are achieved by adopting a lap joint mode between the cover plates along the circumferential direction, the cover plates are lapped with mounting openings at the upper edge of the groove through dovetail-shaped lugs with front and rear reserved semi-open holes and are fixed through pressing nails, the heat-proof dimensional cover covers the integrated air bag and is fixed on an aircraft shell in the front and rear directions along the axis direction of a missile, and the integrated air bag is ejected when being unfolded and then moves backwards under the action of incoming flow.
2. The integrated airbag deceleration device for interstage separation of an aircraft according to claim 1, wherein the diameter of the integrated airbag after being inflated and deployed is determined by the formula:
the S-integrated airbag is used for completely unfolding the added windward area, the D-integrated airbag is used for expanding the diameter of the inflated airbag, the D is the diameter of the lower windward section of the aircraft, and the determination formula of the S is as follows:
f is the increased pneumatic resistance when the integrated air bag is completely unfolded,
is a dynamic pressure of upper and lower separation points of the aircraft,
the residual thrust of the engine of the lower aircraft after the aircraft is separated.
3. The integrated air bag speed reducer for interstage separation of the aircraft according to claim 2, wherein a skirt-shaped mounting structure arranged outside the integrated air bag is matched with a pressing ring matched with the skirt-shaped mounting structure in the fixed supporting structure to fixedly connect the integrated air bag with the fixed supporting structure.
4. An integrated air bag retarder for interstage separation of an aircraft according to claim 1 wherein the number of gas generators and the effective gas output are selected based on the nominal inflation volume of the air bag.
5. The integrated air bag speed reducer for interstage separation of the aircraft according to claim 1, wherein the fixed supporting structure is provided with a through hole at the part where the integrated air bag air inlet is connected with the air outlet of the gas generator, and an inflation pipe opening structure is arranged to enable the integrated air bag air inlet to be in sealing butt joint with the air outlet of the gas generator, so that the integrated air bag is ensured not to leak during inflation.
6. A method of designing an integrated airbag deceleration device for interstage separation of aircraft according to any of claims 1 to 5, characterized in that the method comprises the following steps:
calculating to obtain the deployment diameter and the nominal filling volume of the integrated airbag according to the flying height and speed of the aircraft at the separation moment, the residual thrust of the engine at the lower stage and the diameter of the windward section of the lower stage;
determining the configuration number and the effective gas output of the gas generators according to the nominal filling volume and the volume of the tail cabin of the lower stage of the aircraft;
determining the shape of the integrated airbag according to the deployment diameter of the integrated airbag;
determining the material of the integrated air bag according to the dynamic pressure and the atmospheric pressure at the separation moment of the aircraft;
determining the folding mode and the installation and fixation mode of the integrated air bag according to the shape and the material of the integrated air bag;
determining the number of inflation ports of the integrated air bag and the connection mode of the inflation ports and the air outlets of the gas generators according to the number of the gas generators;
determining the shape of the heat-proof dimensional cover, the number of cover plates and the installation mode of the cover plates according to the appearance of the lower level of the aircraft;
and determining the material and the surface treatment mode of the heat-proof dimensional cover according to the external temperature and strength requirements before the separation of the aircraft.
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