A reentry vehicle multi-position thermal protection device and a control method thereof

Abstract

The application provides a reentry vehicle multi-position thermal protection device and a control method thereof. The protection device comprises a load cabin, a protection member arranged at the front end of the load cabin, the front end of the protection member constituting a head of the vehicle, and the tail end of the protection member constituting a shoulder of the vehicle, wherein the head is provided with one or more head jet holes, and the shoulder is provided with one or more shoulder jet holes; and a jet device arranged in the protection member and selectively communicated with the head jet holes and the shoulder jet holes, used for spraying gas to the head jet holes and / or the shoulder jet holes to form thermal protection for the head and / or the shoulder. The application can form jet thermal protection for the head and the shoulder of the vehicle.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a multi-position thermal protection device of a reentry aircraft and a control method thereof. BACKGROUND

[0002] With the development of space industry, the earth-to-space transportation and deep space exploration will be the focus of future research. Compared with the traditional reentry deceleration method and the inflatable reentry aircraft, the mechanical deployment type reentry aircraft has the advantages of small envelope constraint, high carrying efficiency and good deceleration effect, and has attracted much attention at home and abroad in recent years. The reentry process of the reentry aircraft passes through the rarefied flow, the transition flow and the continuous flow region in turn, and a large amount of aerodynamic heat is generated during high-speed flight, which causes ablation to the surface of the aircraft and the overall aircraft. How to effectively and reasonably protect the reentry aircraft from heat is one of the problems to be solved.

[0003] In recent years, many domestic and foreign scholars have proposed many methods for reducing drag and preventing heat, such as reverse jet flow, adding a drag-reducing rod, adding a pneumatic disc, a wind-facing cavity, energy deposition, and many combinations. For example, the related art uses a drag-reducing rod and a pneumatic disc to reduce drag and prevent heat.

[0004] The existing heat protection methods have many problems. If the jet flow is used for heat protection, the working medium occupies a large space inside the aircraft. If a device is added, it is exposed to the outer end of the aircraft and is severely ablated, and it affects the shape and center of mass of the reentry aircraft. At the same time, the existing heat protection is a single method for protecting the head of the reentry aircraft, and the overall aircraft protection effect is not good. SUMMARY

[0005] The purpose of the embodiments of the present application is to provide a multi-position thermal protection device of a reentry aircraft and a control method thereof, to solve the problem that the existing technology can only protect the head of the reentry aircraft in a single way, resulting in poor overall aircraft protection effect.

[0006] The embodiments of the present application provide a multi-position thermal protection device of a reentry aircraft, comprising: a payload cabin; a protection piece arranged at the front end of the payload cabin, the front end of the protection piece constituting the head of the aircraft, and the tail end of the protection piece constituting the shoulder of the aircraft, wherein the head is provided with one or more head jet flow holes, and the shoulder is provided with one or more shoulder jet flow holes; a jet flow device arranged in the protection piece and selectively communicated with the head jet flow hole and the shoulder jet flow hole, for spraying gas to the head jet flow hole and / or the shoulder jet flow hole, so as to form thermal protection for the head and / or the shoulder.

[0007] The head jet flow hole and the shoulder jet flow hole are arranged at the head and the shoulder of the aircraft respectively, the jet flow device is arranged in the interior of the protection member, the jet flow device can respectively spray gas to the head jet flow hole and the shoulder jet flow hole to form omnibearing heat protection for the shoulder and the head in multiple positions, the coverage position is more comprehensive, and the heat protection effect is better. Meanwhile, the interior space of the protection member is used to carry medium jet flow to perform overall heat protection for the aircraft, the space utilization is improved, and the original load carrying of the aircraft is not affected.

[0008] In some embodiments, the jet flow device comprises a jet flow gas cylinder having a first gas outlet end and a second gas outlet end, the first gas outlet end is communicated with the head jet flow hole through a first control valve, and the second gas outlet end is communicated with the shoulder jet flow hole through a second control valve.

[0009] The reentry aircraft multi-position heat protection device of the embodiment of the application arranges double jet flow gas cylinders in the protection member, one jet flow gas cylinder can respectively spray gas to the head jet flow hole and the shoulder jet flow hole to form omnibearing heat protection for the shoulder and the head in multiple positions, the coverage position is more comprehensive, and the heat protection effect is better.

[0010] In some embodiments, the jet flow device can be provided with a plurality of jet flow devices, the plurality of jet flow devices are arranged in the circumferential direction of the protection member and correspond to the plurality of head jet flow holes and the plurality of shoulder jet flow holes one by one. The plurality of jet flow devices respectively spray from the corresponding head jet flow hole and / or the corresponding shoulder jet flow hole to form omnibearing heat protection for the shoulder and the head of the aircraft in multiple positions.

[0011] In some embodiments, the first control valve is a first flow regulating control valve, and the first flow regulating control valve is communicated between the first gas outlet end and the head jet flow hole.

[0012] In the embodiment of the application, the first flow regulating control valve is used to regulate the gas flow from the first gas outlet end of the jet flow gas cylinder to the head jet flow hole.

[0013] In some embodiments, the second control valve is a second flow regulating control valve, and the second flow regulating control valve is communicated between the second gas outlet end and the shoulder jet flow hole.

[0014] In the embodiment of the application, the first flow regulating control valve and the second flow regulating control valve are arranged, more gas flow can be distributed to the position that is more needed, the reverse jet flow is more efficient and reasonable. And the jet flow flow can be regulated in real time, the regulation mode is simple and fast in response.

[0015] In some embodiments, the jet flow device further comprises a connecting hose communicated between the head jet flow hole and the first flow regulating control valve.

[0016] The connecting hose has flexibility, and can be stretched and bent when the reentry vehicle is unfolded, thereby improving the reliability of gas flow.

[0017] In some embodiments, one end of the first flow regulating control valve is fixed to the first gas outlet end of the jet flow gas cylinder, the other end of the first flow regulating control valve is communicated with one end of the connecting hose through a first adapter, and the other end of the connecting hose is communicated with the head jet flow hole; one end of the second flow regulating control valve is fixed to the second gas outlet end of the jet flow gas cylinder, and the other end of the second flow regulating control valve is communicated with the shoulder jet flow hole through a second adapter.

[0018] In the embodiments, the first adapter and the second adapter are used to collect and buffer the gas flowing out of the control valve.

[0019] In some embodiments, a hollow cavity is formed in the protective member, and the jet flow device is arranged in the hollow cavity.

[0020] In some other embodiments, the protective member comprises a plurality of unfolding rods arranged around the outer peripheral wall of the payload cabin, and the plurality of unfolding rods are rotatable relative to the payload cabin to make the protective member in an unfolded state; and the jet flow device is arranged in the unfolding rods.

[0021] In the embodiments, the double-opening jet flow gas cylinder is arranged in the unfolding rods of the protective member, and one jet flow gas cylinder can respectively spray gas to the head jet flow hole and the shoulder jet flow hole to form all-around thermal protection for the shoulder and the head, so that the coverage is more comprehensive, and the thermal protection effect is better. Meanwhile, the internal space of the unfolding rods is used to carry out the whole thermal protection of the vehicle by medium jet flow, so that the space utilization is improved, and the original payload carrying of the vehicle is not affected.

[0022] In some embodiments, the unfolding mechanism comprises a connecting rod and a sliding block, the front end of the unfolding rod is hinged to the payload cabin, a sliding channel is arranged on the unfolding rod, one end of the connecting rod is hinged to the payload cabin, the other end of the connecting rod is connected with the sliding block, and the sliding block is slidingly connected with the sliding channel. In the embodiments, the unfolding of the protective member is realized by the unfolding mechanism, and the unfolding process is more stable.

[0023] Further, the protective member further comprises a skin connected with each of the unfolding rods, and the skin is arranged in the umbrella-shaped head of the payload cabin, wherein the skin is folded and unfolded together with the protective member.

[0024] In the embodiments, the first lifting lug and the second lifting lug are respectively hinged to the unfolding rods and the connecting rod, so that the unfolding rods do not interfere with the payload cabin during the unfolding process, and the installation is convenient.

[0025] The application further provides a control method of a multi-position thermal protection device of a reentry vehicle, which is applied to the thermal protection device in any of the above embodiments, and the method comprises the following steps: during a flight task of the vehicle, the first control valve and / or the second control valve are controlled to spray the jet gas from the jet gas bottle to the head jet hole and / or the shoulder jet hole of the vehicle, so that the shoulder and / or the head of the vehicle are formed with thermal protection.

[0026] In some embodiments, the step of, during the flight task of the vehicle, controlling the first control valve and / or the second control valve to spray the jet gas from the jet gas bottle to the head jet hole and / or the shoulder jet hole of the vehicle, so that the shoulder and / or the head of the vehicle are formed with thermal protection, comprises the following steps: during the flight task of the vehicle, the first control valve and / or the opening degree of the first control valve are controlled according to the thermal parameter of the head of the vehicle and / or the thermal parameter of the shoulder, so as to adjust the flow of the jet gas sprayed from the jet gas bottle to the head jet hole and / or the shoulder jet hole of the vehicle, wherein the thermal parameter comprises a surface temperature and / or a heat flux density. BRIEF DESCRIPTION OF DRAWINGS

[0027] In order to more clearly illustrate the technical solutions of the embodiments of the application, the following will briefly introduce the drawings needed to be used in the embodiments of the application. It should be understood that the following drawings only show some of the embodiments of the application, and therefore should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can also be obtained without creative labor on the basis of these drawings.

[0028] Figure 1 A perspective view of a multi-position thermal protection device of a reentry vehicle is provided for the first embodiment of the application;

[0029] Figure 2 A partial cross-sectional view of a protection piece of a multi-position thermal protection device of a reentry vehicle is provided for the first embodiment of the application;

[0030] Figure 3 A cross-sectional view of a multi-position thermal protection device of a reentry vehicle is provided for the first embodiment of the application;

[0031] Figure 4 A cross-sectional view of a micro ball valve of a multi-position thermal protection device of a reentry vehicle is provided for the first embodiment of the application;

[0032] Figure 5 A perspective view of a multi-position thermal protection device of a reentry vehicle is provided for the second embodiment of the application;

[0033] Figure 6 Another perspective view of a multi-position thermal protection device of a reentry vehicle is provided for the second embodiment of the application;

[0034] Figure 7 A deployment mechanism of a multi-position thermal protection device of a reentry vehicle according to a second embodiment of the present application is shown in the figure;

[0035] Figure 8 A control method of a multi-position thermal protection device of a reentry vehicle according to an embodiment of the present application is shown in the figure;

[0036] Figure 9 A working process of a multi-position thermal protection device of a reentry vehicle according to an embodiment of the present application is shown in the figure. DETAILED DESCRIPTION

[0037] The technical solutions in the embodiments of the present application will be described below with reference to the accompanying drawings.

[0038] It should be noted that similar reference numerals and letters refer to similar items in the following drawings, and therefore, once an item is defined in one drawing, it need not be further defined and explained in subsequent drawings. Meanwhile, in the description of the present application, the terms "first", "second", etc. are only used for distinguishing description, and cannot be understood as indicating or implying relative importance.

[0039] The embodiments of the present application provide a multi-position thermal protection device of a reentry vehicle, which can realize thermal protection of the head and / or shoulder of the vehicle by forming jet flow, and can adjust and control the flow of jet flow in different positions according to the severity of the head and shoulder heat flow to achieve the purpose of efficient protection.

[0040] Reference Figure 1 and Figure 2 , Figure 1 A perspective view of a multi-position thermal protection device of a reentry vehicle according to an embodiment of the present application is shown in the figure; Figure 2 A partial cross-sectional view of a protection member of a multi-position thermal protection device of a reentry vehicle according to an embodiment of the present application is shown in the figure.

[0041] The multi-position thermal protection device of a reentry vehicle provided by the embodiments of the present application comprises a load cabin 10, a protection member 20 and a jet flow device 30.

[0042] The load cabin 10 is internally used for providing load, and the load cabin 10 can be, for example, in a cylindrical shape.

[0043] The protection member 20 is arranged at the front end of the load cabin 10, the front end of the protection member 20 constitutes the head 201 of the vehicle, and the tail end of the protection member 20 constitutes the shoulder 202 of the vehicle, wherein the head 201 is provided with one or more head jet flow holes 21, and the shoulder 202 is provided with one or more shoulder jet flow holes 22. The protection member 20 can be in an umbrella shape for providing thermal protection for the head of the vehicle during flight.

[0044] The fluid jet device 30 is arranged in the shield 20 and is in selective communication with the head fluid jet hole 21 and the shoulder fluid jet hole 22 respectively, for spraying gas to the head fluid jet hole 21 and / or the shoulder fluid jet hole 22 to form thermal protection for the head 201 and / or the shoulder 202. The selective communication means that the communication passage between the fluid jet device 30 and the head fluid jet hole 21 can be opened or closed, and the communication passage between the fluid jet device 30 and the shoulder fluid jet hole 22 can be opened or closed. In an example, when thermal protection for the head is needed, the communication passage between the fluid jet device 30 and the head fluid jet hole 21 can be selected to be opened, so that the gas sprayed by the fluid jet device 30 is jetted out of the head fluid jet hole 21 to form thermal protection for the head 201. In another example, when thermal protection for the shoulder is needed, the communication passage between the fluid jet device 30 and the shoulder fluid jet hole 22 can be selected to be opened, so that the gas sprayed by the fluid jet device 30 is jetted out of the shoulder fluid jet hole 22 to form thermal protection for the shoulder 202. In yet another example, when thermal protection for the head and the shoulder is needed, the communication passage between the fluid jet device 30 and the head fluid jet hole 21 can be selected to be opened, and the communication passage between the fluid jet device 30 and the shoulder fluid jet hole 22 can be selected to be opened, so that the gas sprayed by the fluid jet device 30 is jetted out of the head fluid jet hole 21 and the shoulder fluid jet hole 22 to form thermal protection for the head 201 and the shoulder 202.

[0045] The reentry vehicle multi-position thermal protection device of the embodiment of the present application forms omnidirectional thermal protection for the shoulder and the head in multiple positions by arranging the head fluid jet hole 21 and the shoulder fluid jet hole 22 in the head and the shoulder of the vehicle respectively, and arranging the fluid jet device 30 in the interior of the shield 20, which can spray gas to the head fluid jet hole 21 and the shoulder fluid jet hole 22 respectively to form omnidirectional thermal protection for the shoulder and the head in multiple positions, so that the coverage position is more comprehensive and the thermal protection effect is better. Meanwhile, the interior space of the shield 20 is used to carry medium fluid jet to form overall thermal protection for the vehicle, which improves the space utilization rate and does not affect the original load carrying of the vehicle.

[0046] In some embodiments, reference is made to Figure 3 , Figure 3A cross-sectional view of a multi-position thermal protection device of a reentry vehicle is provided in the embodiments of the present application. The jet flow device 30 includes a jet flow gas cylinder 31, which can be a double-opened cylinder, having a first gas outlet end and a second gas outlet end. The first gas outlet end is in communication with the head jet flow hole 21 through a first control valve 32, and the second gas outlet end is in communication with the shoulder jet flow hole 22 through a second control valve 33. The jet flow gas cylinder 31 stores high-pressure gas, and the selective jet flow of the high-pressure gas in the jet flow gas cylinder 31 to the head jet flow hole 21 and / or the shoulder jet flow hole 22 can be controlled by controlling the opening and closing of the first control valve 32 and the second control valve 33, so as to selectively jet gas to the head jet flow hole 21 and / or the shoulder jet flow hole 22 to perform jet flow thermal protection on the head 201 and / or the shoulder 202. For example, the jet flow gas cylinder 31 can be a cylindrical gas cylinder, which carries jet flow gas with a certain pressure inside. The gas medium can be nitrogen, oxygen, carbon dioxide, etc. The pressure and gas storage capacity of the gas cylinder can be designed and calculated according to the flight conditions.

[0047] During the flight mission of the vehicle, there can be multiple modes of reverse jet flow. For example, when the thermal environment near the head 201 of the vehicle is relatively severe, head jet flow is needed. At this time, the first control valve 32 can be opened, and the high-pressure gas in the jet flow gas cylinder 31 is jetted out from the head jet flow hole 21 to push the shock wave away from the surface of the vehicle, thereby reducing the heat flux density on the surface of the vehicle and improving the thermal environment of the head, forming thermal protection of the head. When a large amount of aerodynamic heat is gathered on the shoulder 202 of the vehicle, shoulder jet flow is needed. The second control valve 33 can be opened, and the high-pressure gas in the jet flow gas cylinder 31 is jetted out from the shoulder jet flow hole 22 to reduce the local heat flux density of the shoulder and improve the thermal environment of the shoulder, forming thermal protection of the shoulder. When the head and the shoulder need to be thermally protected at the same time, the first control valve 32 and the second control valve 33 are controlled to be opened at the same time. At this time, the gas in the jet flow gas cylinder 31 is jetted out from the head jet flow hole 21 and the shoulder jet flow hole 22 at the same time, achieving the effect of multi-position thermal protection.

[0048] The multi-position thermal protection device of the reentry vehicle in the embodiments of the present application can set a double-opened jet flow gas cylinder 31 in the protection member 20, and one jet flow gas cylinder can jet gas to the head jet flow hole 21 and the shoulder jet flow hole 22 respectively to form all-around thermal protection on the shoulder and the head in multiple positions, which is more comprehensive in position coverage and has better thermal protection effect.

[0049] In some embodiments, multiple jet flow devices 30 can be provided, and the multiple jet flow devices 30 are arranged in the circumferential direction of the protection member 20 and correspond to multiple head jet flow holes 21 and multiple shoulder jet flow holes 22 one by one. The multiple jet flow devices 30 respectively jet out from the corresponding head jet flow holes 21 and / or the corresponding shoulder jet flow holes 22 to form all-around thermal protection on the shoulder and the head of the vehicle in multiple positions.

[0050] In some embodiments, the first control valve 32 may be a first flow rate regulating control valve, and the first flow rate regulating control valve is connected between the first gas outlet end and the head jet holes; and / or, the second control valve 33 may be a second flow rate regulating control valve, and the second flow rate regulating control valve is connected between the second gas outlet end and the shoulder jet holes.

[0051] The first flow rate regulating control valve may, for example, be a micro ball valve ( Figure 4 as shown), and the motor of the micro ball valve is used to control the rotation of the ball core of the ball valve to adjust the opening degree of the air flow passage, so as to adjust the air flow rate flowing from the first gas outlet end of the jet gas cylinder to the head jet holes. The second flow rate regulating control valve may also be a micro ball valve, for example, and the motor of the micro ball valve is used to control the rotation of the ball core of the ball valve to adjust the opening degree of the air flow passage, so as to adjust the air flow rate flowing from the second gas outlet end of the jet gas cylinder to the shoulder jet holes.

[0052] The above air flow rate regulation can have multiple modes. For example, during the flight of the aircraft, when the head heat flux density Qo obtained by feedback from the temperature or heat flux sensor attached to the surface of the aircraft is greater than the shoulder heat flux density Qr, that is, Qo > Qr, at this time, more gas jet flow rate needs to be allocated to the head. The opening degree of the first flow rate regulating control valve can be increased, and the opening degree of the second flow rate regulating control valve can be decreased to allocate more jet gas flow rate to the head jet. Another example is that when the head heat flux density Qo obtained by feedback from the temperature or heat flux sensor attached to the surface of the aircraft is less than the shoulder heat flux density Qr, that is, Qo < Qr, more gas jet flow rate needs to be allocated to the shoulder. The opening degree of the first flow rate regulating control valve can be decreased, and the opening degree of the second flow rate regulating control valve can be increased to allocate more jet gas flow rate to the shoulder jet. Another example is that when the head and shoulder heat flux densities are not much different, Qo = Qr, the opening degrees of the first flow rate regulating control valve and the second flow rate regulating control valve can be controlled to be the same. Through the above operations, more gas flow rate can be allocated to the more needed position, making the reverse jet more efficient and reasonable. And the jet flow rate can be adjusted in real time, and the adjustment method is simple and the response is fast.

[0053] In some embodiments, the jet device 30 further includes a connecting hose 36 connected between the head jet holes 21 and the first flow rate regulating control valve.

[0054] In the embodiments of the present application, the gas ejected from the first gas outlet end of the jet gas cylinder is transported to the head jet holes 21 through the connecting hose 36, so as to form thermal protection at the head. The connecting hose 36 has a certain flexibility, and the connecting hose can be telescoped and bent when the reentry vehicle is deployed, improving the reliability.

[0055] In some embodiments, the first flow regulating control valve is fixed at one end to the first gas outlet of the jet gas bottle 31, for example, by screwing, and is in communication with one end of the connecting hose 36 at the other end through the first adapter 34, for example, by interference fit, and the other end of the connecting hose 36 is in communication with the head jet hole 21. The second flow regulating control valve is fixed at one end to the second gas outlet of the jet gas bottle 31, for example, by screwing, and is in communication with the shoulder jet hole through the second adapter 35. The first adapter 34 and the second adapter 35 are used to collect and buffer the gas flowing out of the control valve.

[0056] For example, the first flow regulating control valve and the second flow regulating control valve can be micro ball valves. The valve core can be rotated by swinging the motor rocker of the micro ball valve to achieve different flow areas, adjust the opening degree, and then adjust the size of the gas flow, thereby playing a flow regulating role. When the ball valve is completely closed, the gas flow can also be blocked.

[0057] In some embodiments, with reference to Figure 3 , the protective member 20 is an internal hollow structure having an internal hollow cavity 203, and the jet device 30 is arranged in the hollow cavity 203. In this embodiment, the protective member 20 can be fixed or unfolded. For example, when the protective member 20 is an unfolded hollow structure, the protective member 20 can be made of flexible material.

[0058] In other embodiments, with reference to Figure 5 and Figure 6 , the protective member 20 surrounds the outer periphery of the payload cabin 10, and the protective member 20 has a folded state of being folded on the outer peripheral wall of the payload cabin 10 and an unfolded state of extending outward relative to the outer peripheral wall of the payload cabin 10. The protective member 20 can be folded or unfolded, and the protective member 20 is in the folded state during the launch and on-orbit operation of the aircraft, and the protective member 20 is in the unfolded state during the reentry process of the aircraft. In the folded state, the protective member 20 and the payload cabin 10 are substantially cylindrical as a whole, and in the unfolded state, the protective member 20 and the payload cabin 10 are separated and substantially umbrella-shaped as a whole.

[0059] Specifically, the protective member 20 includes a plurality of unfolding rods 23 arranged around the outer peripheral wall of the payload cabin 10, and the plurality of unfolding rods 23 are rotatable relative to the payload cabin 10 to make the protective member 20 in the unfolded or folded state. More specifically, the plurality of unfolding rods 23 can be uniformly arranged around the outer periphery of the payload cabin 10, and the structures of the unfolding rods can be the same, for example, hollow rods, which are convenient for storing medium gas inside and reduce the overall weight. The front end of each unfolding rod 23 is movably connected to the outer peripheral wall of the payload cabin 10, and the rear end is a free end, and the rear ends of the plurality of unfolding rods 23 form the shoulder of the aircraft.

[0060] In some embodiments, with reference toFigure 7 The protection member 20 can be unfolded by an unfolding mechanism, which comprises a connecting rod 41 and a sliding block. The front end of the unfolding rod 23 is hinged to the load cabin 10, and the unfolding rod 23 is provided with a sliding channel. One end of the connecting rod 41 is hinged to the load cabin 10, and the other end is connected to the sliding block, which is in sliding connection with the sliding channel.

[0061] Further, the load cabin 10 is provided with a first lifting lug 42 and a second lifting lug 43 arranged axially and spaced apart. The front end of the unfolding rod 23 is hinged to the load cabin 10 through the first lifting lug 42, and the connecting rod is hinged to the load cabin 10 through the second lifting lug 43. The first lifting lug 42 and the second lifting lug 43 are respectively hinged to the unfolding rod 23 and the connecting rod 41, which avoids interference with the load cabin 10 during the unfolding of each unfolding rod and is easy to install.

[0062] In some embodiments, referring to Figure 5 and Figure 6 The protection member 20 further comprises a skin connected to each unfolding rod 43, which covers the umbrella-shaped head of the load cabin, wherein the skin follows the folding and unfolding of the protection member. The skin comprises a head cone-shaped heat protection surface connected to the front end of each unfolding rod and a pneumatic deceleration surface connected to the front end and the tail end of each unfolding rod and connected to the heat protection surface. The heat protection surface and the pneumatic deceleration surface provide overall heat protection for the aircraft.

[0063] In summary, the reentry aircraft multi-position heat protection device of the embodiments has the following beneficial effects:

[0064] (1) The reentry aircraft multi-position (head and shoulder) heat protection device can simultaneously perform reverse jet heat protection, which has better heat protection effect and more comprehensive coverage.

[0065] (2) The flow can be adjusted by the control valve, and based on the heat flux density of the head and the shoulder, more gas flow is allocated to the position in need, so that the reverse jet is more efficient.

[0066] (3) During operation, the jet flow can be adjusted in real time, and the adjustment method is simple and fast.

[0067] (4) The overall structure is small and exquisite, and can be placed in the space of the aircraft itself without occupying additional load cabin space, which has high utilization rate.

[0068] The embodiments of the present application also provide a control method for a reentry aircraft multi-position heat protection device, which is applied to the heat protection device mentioned above, referring to Figure 8 and Figure 9 The method comprises step S11.

[0069] In step S11, during the flight task of the aircraft, the ejection bottle is controlled to spray the ejection gas to the head ejection hole and / or the shoulder ejection hole of the aircraft to form a thermal protection for the shoulder and / or the head of the aircraft.

[0070] With reference to Figure 9 The specific control method of the multi-position thermal protection device of the reentry aircraft is as follows:

[0071] Initialization process: the initial state is that the first control valve 321 (for example, ball valve A) and the second control valve 322 (for example, ball valve B) are closed, and the gas working substance with a certain pressure is stored in the double-opening ejection bottle 31, so as to facilitate the reverse ejection.

[0072] Normal working process: during the normal working process, there are multiple modes for reverse ejection:

[0073] a. Head ejection: during the flight task of the aircraft, when the thermal environment near the head is relatively severe, head ejection is needed. At this time, the first control valve 321 (for example, ball valve A) is controlled to be opened, for example, the ball valve core is rotated by the motor of the first micro ball valve, the valve core is opened, the high-pressure gas passes through the micro ball valve, the adapter, the connecting hose, and is sprayed out through the head ejection hole, the shock wave of the head of the aircraft is pushed away from the surface of the aircraft, thereby reducing the heat flux density of the surface of the aircraft and improving the thermal environment of the head.

[0074] b. Shoulder ejection: during the flight task, when a large amount of aerodynamic heat is gathered on the shoulder of the aircraft, shoulder ejection is performed. At this time, the second control valve 322 (for example, ball valve B) is controlled to be opened, for example, the ball valve is opened by the second micro ball valve, the high-pressure gas passes through the second micro ball valve and the second adapter and is sprayed out through the shoulder ejection hole, thereby reducing the local heat flux density of the shoulder.

[0075] c. Head + shoulder cooperative ejection: when the head and the shoulder need to be thermally protected during the flight task, the first control valve 321 (for example, ball valve A) and the second control valve 322 (for example, ball valve B) are controlled to be opened at the same time by the motor of the first micro ball valve and the second micro ball valve. At this time, the gas in the ejection bottle is sprayed out from the head ejection hole and the shoulder ejection hole at the same time through the two ends, thereby achieving the effect of multi-position thermal protection.

[0076] In some embodiments, step S11 comprises:

[0077] During the flight task of the aircraft, according to the thermal parameters of the head and / or the thermal parameters of the shoulder of the aircraft, the first control valve and / or the opening degree of the first control valve are controlled to adjust the flow of the ejection gas sprayed by the ejection bottle to the head ejection hole and / or the shoulder ejection hole of the aircraft, wherein the thermal parameters include the surface temperature and / or the heat flux density.

[0078] With reference to Figure 9, the specific flow regulation process is as follows: the flow can be regulated by the opening of the first micro ball valve and the second micro ball valve, and there are multiple cases:

[0079] a. Qo>Qr, assuming that the head heat flux density Qo obtained by the temperature or heat flux sensor attached to the surface of the aircraft during flight is greater than the shoulder heat flux density Qr, at this time, more gas jet flow should be allocated to the head, so the opening of the first micro ball valve (for example, ball valve A) is increased, and the opening of the second micro ball valve (for example, ball valve B) is reduced, and the flow regulation is realized by the above operation, realizing more efficient and reasonable reverse jet flow.

[0080] b. Qo<Qr, contrary to case a, when the shoulder heat flux density is greater, the opening of the first micro ball valve (for example, ball valve A) is reduced, and the opening of the second micro ball valve (for example, ball valve B) is increased, to allocate more jet gas flow to the shoulder jet.

[0081] c. Qo=Qr, when the head and shoulder heat flux densities are similar, the openings of the two ball valves (for example, ball valve A and ball valve B) can be maintained consistent.

[0082] The end of the work process is as follows: when the heat protection requirement is met or the jet gas is consumed, the work is ended, at this time, the first micro ball valve (for example, ball valve A) and the second micro ball valve (for example, ball valve B) are completely closed, and the work is ended.

[0083] In several embodiments provided in the present application, it should be understood that the disclosed devices and methods can also be implemented in other ways. The device embodiments described above are only schematic, for example, the flowchart and block diagram in the drawings show the possible implementation architecture, function and operation of the device, method and computer program product according to the embodiments of the present application. In this regard, each block in the flowchart or block diagram can represent a module, a program segment or a part of code, which contains one or more executable instructions for implementing the specified logical function. It should also be noted that in some alternative implementations, the functions noted in the blocks can occur in different orders than that shown in the drawings. For example, two consecutive blocks can actually be executed substantially in parallel, and sometimes they can be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagram and / or flowchart, and the combination of blocks in the block diagram and / or flowchart, can be implemented by a dedicated hardware-based system for executing the specified functions or actions, or can be implemented by a combination of dedicated hardware and computer instructions.

[0084] In addition, each functional module in each embodiment of the present application can be integrated together to form an independent part, or each module can exist independently, or two or more modules can be integrated to form an independent part.

[0085] If the functions are implemented in the form of software function modules and sold or used as independent products, they can be stored in a computer readable storage medium. Based on this understanding, the technical solutions of the present application essentially or the parts that make contributions to the prior art or parts of the technical solutions can be embodied in the form of a software product. The computer software product is stored in a storage medium and includes several instructions for causing a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in each embodiment of the present application. The aforementioned storage medium includes: a U disk, a mobile hard disk, a read-only memory (ROM, Read-Only Memory), a random access memory (RAM, Random Access Memory), a magnetic disk or an optical disk, and various program code storage media.

[0086] The above is only an embodiment of the present application and does not limit the protection scope of the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application. It should be noted that similar reference numbers and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0087] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto. Any skilled person in the art can easily think of changes or replacements within the technical range disclosed by the present application, which shall be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the scope of the right protection.

[0088] It is to be noted that, as used in this specification and the appended claims, the singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise. Thus, for example, reference to "a component" can include a combination of two or more components. Additionally, the terms "comprise," "comprises," and "comprising," or any variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements is not necessarily limited to those elements, but can include other elements not expressly listed or inherent to such process, method, article, or apparatus. Furthermore, unless otherwise indicated herein, the terms "first," "second," "third," etc., are used herein merely as labels, and are not intended to impose ordinal import.

Claims

1. A multiple position thermal protection system for a reentry vehicle, comprising: The application relates to a multi-position thermal protection device for a reentry vehicle, comprising: a load cabin; a protection member arranged at the front end of the load cabin, the front end of the protection member constituting the head of the vehicle, and the tail end of the protection member constituting the shoulder of the vehicle, wherein the head is provided with one or more head ejection holes, and the shoulder is provided with one or more shoulder ejection holes; a plurality of ejection devices arranged in the protection member, each of the ejection devices being selectively communicated with the head ejection hole and the shoulder ejection hole, and used for spraying gas to the head ejection hole and / or the shoulder ejection hole, so as to form thermal protection for the head and / or the shoulder; the protection member comprises a plurality of unfolding rods arranged around the peripheral wall of the load cabin, the plurality of unfolding rods being rotatable relative to the load cabin, so that the protection member is in an unfolded state; and the ejection devices are arranged in the unfolding rods.

2. The multi-position thermal protection device for a reentry vehicle according to claim 1, wherein the ejection device comprises an ejection gas cylinder, the ejection gas cylinder has a first gas outlet end and a second gas outlet end, the first gas outlet end is communicated with the head ejection hole through a first control valve, and the second gas outlet end is communicated with the shoulder ejection hole through a second control valve.

3. The multi-position thermal protection device for a reentry vehicle according to claim 2, wherein the first control valve is a first flow regulating control valve, and the first flow regulating control valve is communicated between the first gas outlet end and the head ejection hole; and / or the second control valve is a second flow regulating control valve, and the second flow regulating control valve is communicated between the second gas outlet end and the shoulder ejection hole.

4. The multi-position thermal protection device for a reentry vehicle according to claim 3, wherein the ejection device further comprises a connecting hose communicated between the head ejection hole and the first flow regulating control valve.

5. The multi-position thermal protection device for a reentry vehicle according to claim 4, wherein one end of the first flow regulating control valve is fixed to the first gas outlet end of the ejection gas cylinder, the other end of the first flow regulating control valve is communicated with one end of the connecting hose through a first adapter, and the other end of the connecting hose is communicated with the head ejection hole; and one end of the second flow regulating control valve is fixed to the second gas outlet end of the ejection gas cylinder, and the other end of the second flow regulating control valve is communicated with the shoulder ejection hole through a second adapter.

6. The multi-position thermal protection device for a reentry vehicle according to claim 1, wherein the plurality of ejection devices are arranged in the circumferential direction of the protection member and correspond to the plurality of head ejection holes and the plurality of shoulder ejection holes one by one. The method is applied to the thermal protection device according to any one of claims 2-5, and the method comprises the following steps: during the flight task of the vehicle, the ejection device sprays ejection gas to the head ejection hole and / or the shoulder ejection hole of the vehicle by controlling the first control valve and / or the second control valve, so as to form thermal protection for the shoulder and / or the head of the vehicle. ​ ​ ​ ​ ​ 7. A method of controlling a multi-position thermal protection system of a reentry vehicle, characterized in that, ​ ​ 8. The control method of the reentry vehicle multi-position thermal protection device according to claim 7, wherein the controlling the first control valve and / or the second control valve to make the fluidic device spray the fluidic gas to the head fluidic orifice and / or the shoulder fluidic orifice of the vehicle to form the thermal protection for the shoulder and / or the head of the vehicle during the flight mission of the vehicle comprises: controlling the first control valve and / or the opening of the first control valve to adjust the flow rate of the fluidic gas sprayed by the fluidic device to the head fluidic orifice and / or the shoulder fluidic orifice of the vehicle according to the head thermal parameter and / or the shoulder thermal parameter of the vehicle during the flight mission of the vehicle, wherein the thermal parameter comprises the surface temperature and / or the surface heat flux density. ​

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