CN205076051U - Hypersonic vehicle - Google Patents

Abstract

The utility model discloses a can can return used repeatedly's hypersonic vehicle at the sky to the superelevation sound velocity from static acceleration. Realize this kind of hypersonic vehicle, the most important is the engine: a turbofan or turbojet engine cooperation are used that a section can hang down the punching press rocket engine who starts and have now under the mach speed is provided, turbine / the super punching press engine that fires that to external study transform turbine / super punching press rocket engine that fires as, to have afterburning formula turbofan engine now upgrades to turbofan / super punching press rocket engine that fires. Simultaneously become area and the changeable wing of angle with the flight vehicle design and fly under the conditions such as different mach numbers in order to adapt to it, describe high -speed fricative surface design one -tenth frictional force of aircraft and air and the all little rough and uneven in surface sharkskin of aerodynamic heating.

Description

Hypersonic vehicle

[technical field]

The present invention relates to the relevant issues of Aeronautics and Astronautics aircraft, specifically refer to and can accelerate to superelevation velocity of sound from static and reusable aircraft can be returned in empty sky.

[background technology]

We usually within ground 100 kms for aviation, be space flight beyond 100 kms.Realize this hypersonic vehicle, it is essential driving engine, and existing various driving engine has various shortcoming and defect, hypersonic flight cannot be realized: the aircraft of piston type, whirlpool axle, whirlpool oar, whirlpool spray, turbofan, thrust type fanjet can only fly by the maximum M3 of subsonic, transonic and hyprsonic in the scope apart from ground 30 kms.Scramjet engine cannot under static state start voluntarily, thinks and needs to use rocket assist could start to during M4, can not use in exoatmosphere.Rocket engine can use in exoatmosphere, but needs self-contained a large amount of oxidizer and not reproducible use.Studied the composite engine such as turbine/ultra-combustion ramjet and rocket/ultra-combustion ramjet abroad, but the former can only work in endoatmosphere, and due to height off the ground difference, the oxygen content in air is also different, the efficiency of driving engine is difficult to ensure; The rocket of the latter needs self-contained oxidizer and can not whole repeated usage, can not make full use of the oxygen in hyperoxic low latitude.

[summary of the invention]

The object of the invention is to the deficiency avoiding above-mentioned various driving engine, provide one can reusable hypersonic speed driving engine outside endoatmosphere from static to hypersonic.

For achieving the above object, technical scheme of the present invention is: 1, develop a punching press/rocket engine that can start under low Mach velocity and existing turbofan or turbojet engine with the use of; 2, the turbine/scramjet engine studied is transform as turbine/ultra-combustion ramjet/rocket engine abroad; 3, existing thrust type fanjet is upgraded to turbofan/ultra-combustion ramjet/rocket engine.Aircraft is realized from ground static, aerial hyprsonic, high-altitude and space hypersonic flight respectively by above-mentioned three kinds of driving engines.Flight Vehicle Design become the wing of area and variable-angle to fly under the conditions such as different Mach number to adapt to it simultaneously, aircraft is become the rough and uneven in surface sharkskin shape that friction force and Aerodynamic Heating are all little with the surface design of air high-speed friction.

The present invention compared with the existing technology, have the following advantages: 1, can take off as conventional airplane and land because aircraft employs brand-new combination engine, can fly endoatmosphere to superelevation velocity of sound from static, nearly all parts are reusable; 2, the surface design imaging sharkskin due to aircraft and air high-speed friction is rough and uneven in surface like that, not only can reduce flight resistance because reducing the friction force of aircraft and air, Air flow can also be utilized to alleviate Aerodynamic Heating.

[accompanying drawing explanation]

Fig. 1 is the punching press/rocket engine scheme schematic diagram that can start under low Mach velocity;

Fig. 2 is the thrust type fanjet improved a little;

Fig. 3 upgrades to turbine/ultra-combustion ramjet/rocket engine scheme schematic diagram;

Fig. 4 is transformed into turbofan/ultra-combustion ramjet/rocket engine scheme schematic diagram;

Fig. 5 is that scraggly sharkskin shape solid surface and fluid cliding friction analyze schematic diagram.

[detailed description of the invention]

Below in conjunction with accompanying drawing, hypersonic vehicle of the present invention is elaborated:

The punching press that can start under low Mach velocity as shown in Figure 1/rocket engine scheme schematic diagram is that variable geometry inlet Cai Yongjinqidaojihechicunkebianfangshi，Shi Boxihuo [1] and the aircraft that communicated by oxidizer adjustable nozzle [2], oxidizer delivery duct [3] with it are equipped with liquid oxygen or other oxidizer storage tanks [4], fuel oil atomizer [5], tubaeform gas diffusion chamber [6], hollow cone gaseous diffuser [7], hollow cone gas speed reducer [8], combustion chamber [9] and adjustable nozzle [10] successively.The air of certain speed enters from variable geometry inlet Cai Yongjinqidaojihechicunkebianfangshi，Shi Boxihuo [1], atomized fuel mixes from fuel oil atomizer [5] ejection with air, miscellaneous gas is evenly diffused into combustion chamber [9] under the effect of diffuser [7] in diffuser chamber [6], part miscellaneous gas bounce-back under the effect of retarder [8] that cellular breather pipe passes through in diffuser [7] is returned before it and diffuser [7] forms an air mass [11] below, high pressure through being added in diffuser [7] and retarder [8] and their support two ends produces electro spark and to ignite air mass [11] and miscellaneous gas in air mass [11] and between their supports, miscellaneous gas sprays at a high speed from nozzle [10] after Thorough combustion thus produces thrust forward in combustion chamber [9].Owing to there being the existence of the air mass [11] of the slower smooth combustion of speed, how soon the air no matter entering variable geometry inlet Cai Yongjinqidaojihechicunkebianfangshi，Shi Boxihuo [1] has, and also can ensure mixture gas physical efficiency Thorough combustion in combustion chamber [9].

We just can with the thrust type fanjet that improves a little in Fig. 2 with the use of, the air of by-pass air duct and fuel and main duct are not discharged anoxic combustion gas due to traditional thrust type fanjet to separate and cause them to mix at afterburner, afterbunring can be caused insufficient and affect the efficiency of driving engine.We increase a combustion gas collecting chamber [12] and the suitable spout of length or freeing pipe [13] after turbine, the anoxic combustion gas of main duct discharge and the air of by-pass air duct and fuel are separated, together discharges from nozzle [14] after the air and full combustion of fuel of by-pass air duct.Before thrust type fanjet increase by one when this engine stop of high-speed flight work be reduce its to fly resistance and closable triangle inlet channel [15].

The aircraft of punching press/rocket engine that Fig. 1 can start under low Mach velocity and the thrust type fanjet that Fig. 2 improves a little is housed, first start thrust type fanjet and aircraft is accelerated to command speed with time highly, restart the punching press/rocket engine that can start under low Mach velocity together aircraft is accelerated to be not suitable for use thrust type fanjet time closed, continued aircraft to accelerate higher speed and height by punching press/rocket engine, between can according to the oxygen content in air with the increase of height the situation that reduce, this driving engine can regulate the suction quantity of variable geometry inlet Cai Yongjinqidaojihechicunkebianfangshi，Shi Boxihuo [1] and the fuel charge of fuel oil atomizer [5] automatically, also can open simultaneously and adjust oxidizer adjustable nozzle [2] in driving engine, spray into the oxidizers such as the appropriate oxygen through combustion chamber [9] preheating, the work of this driving engine is made to be in optimum regime all the time.When the oxygen content entering into air is not suitable for height and the speed of this engine operation, variable geometry inlet Cai Yongjinqidaojihechicunkebianfangshi，Shi Boxihuo [1] is closed completely, the oxidizers such as the liquid oxygen sprayed by adjustable nozzle [2] continue the fuel combustion sprayed with fuel oil atomizer [5], and at this moment this driving engine has just become the rocket engine that can work in exoatmosphere.

Analyze scramjet engine thrust situation below: suppose that the quality that the unit time enters air by inlet channel [1] is m1, speed is v1, and the area of inlet channel [1] is s1; Spraying into quality of fuel is m2, and the quality of oxidizer is m3, and the speed of combustion gas ejection is v2, and the area of nozzle [10] is s2; Air, fuel and oxidizer are t through the time of driving engine.

Then air acceleration be: a1=(v2-v1)/t,

The acceleration of fuel and oxidizer be: a2=v2/t,

According to Newton's second law, the thrust of combustion gas to nozzle [10] is:

f2＝m1*a1+(m2+m3)*a2

＝m1(v2-v1)/t+(m2+m3)v2/t，

According to pascal's principle: in leakproof tank, the pressure put on static liquid (stream) body will pass to each point with equivalence simultaneously.High-pressure gas to the pressure of container inner wall unit area identical (because the density of combustion gas is very little, the impact of gravity is negligible), to the deboost of inlet channel [1] is: P=f1/s1=f2/s2 then,

Then: f1=f2*s1/s2=[m1 (v2-v1)/t+ (m2+m3) v2/t] * s1/s2,

The thrust of scramjet engine is:

f＝f2-f1

＝m1(v2-V1)/t+(m2+m3)v2/t-[m1(v2-v1)/t+(m2+m3)v2/t]*s1/s2

＝[m1(v2-v1)/t+(m2+m3)v2/t]*(1-s1/s2)，

As can be seen here: the thrust of driving engine is directly proportional to the acceleration/accel of combustion gas through driving engine, namely the area of the air flue that also follows up [1] and nozzle [10] and size, than relevant, also participate in the fuel of work by combustion with combustion gas relevant with the air quality of suction certainly.Want to obtain maximum thrust, the relation of above-mentioned three must be considered.Theoretically simultaneously, as long as have air to continue to enter by inlet channel [1] fuel combustion that combustion chamber [9] and fuel oil atomizer [5] spray to do work and produce acceleration/accel to fuel and air, this driving engine just can normally work generation thrust, just speed is more more fast-forward into the air of inlet channel [1], the fuel of the participation work by combustion that nozzle [5] sprays is more, fuel and oxygen more abundant in combustion chamber [9] (combustion chamber [9] that speed needs sooner the is longer) combustion of suitable length, the speed of combustion gas ejection is faster, thrust is larger, efficiency is higher.The fanjet of whirlpool oar and large bypass ratio is applicable to low-speed operations.Thrust type turbofan, whirlpool spray and scramjet engine are just applicable to hyprsonic and hypersonic flight, we can allow the large-scale and compact electromagnetic on hypersonic vehicle and land and aircraft carrier or combustion-gas catapult use, allow it stride across low speed, directly to take off at a high speed, improve its flight performance, expand its range of use.

As m1=0, v1=0, s1=0, be namely rocket engine mode of operation then its thrust be: f=(m2+m3) v2/t.

Fig. 3 is the turbine/ultra-combustion ramjet/rocket engine scheme schematic diagram of transformation and upgrade on the basis studying turbine/scramjet engine: be modified as by variable geometry inlet Cai Yongjinqidaojihechicunkebianfangshi，Shi Boxihuo and also can close completely and the oxidizer adjustable nozzle [2] increased therein as shown in Figure 1.During low Mach, oxidizer adjustable nozzle [2] is closed completely, and it is exactly turbojet engine, during high Mach, oxidizer adjustable nozzle [2] is opened from being closed to amplify gradually from low discharge completely, it is exactly punching engine, when starting to change, whirlpool spray and punching press can be opened simultaneously, in order to the air of coming in from punching engine and turbojet engine are discharged anoxic combustion gas separately in order to avoid affect the efficiency of driving engine, we increase a combustion gas collecting chamber [16] and the suitable spout of length or freeing pipe [17] equally after turbine, after the spraying nipple [18] of punching engine burns the fuel of atomization and the air mixed firing of coming in, the further Thorough combustion of combustion chamber is evenly diffused into front open circles taper spreading speed reducer [19] through the cone end, and the high-temperature fuel gas group [20] that formation speed is relatively slow between taper spreading speed reducer [19] cone point and freeing pipe [17] is to ensure that combustion gas can not be extinguished, punching engine energy continuous firing, until speed and just closed when being highly not suitable for whirlpool spray and be used alone punching engine, by variable geometry inlet Cai Yongjinqidaojihechicunkebianfangshi，Shi Boxihuo by small size gradually to closing completely, adjustable nozzle [2] is by little to opening completely, and it has just become rocket engine.

Fig. 4 is turbofan/ultra-combustion ramjet/rocket engine scheme schematic diagram that the enterprising step-up level in basis of the thrust type fanjet improved a little at Fig. 2 is transformed into.Between fan and afterburner, correct position increases the switch [22] that an inlet channel that can outwards open [21] and inwardly can close fanjet by-pass air duct.At the oxidizer adjustable nozzle [2] established below as shown in Figure 1 of inlet channel [21].When the maximum speed and height that it can arrive to be delivered to by aircraft by thrust type fanjet, open inlet channel [21], then the switch [22] of by-pass air duct and the triangle inlet channel [15] of fanjet is closed, this Airflow will be walked around fan and enter after the atomized fuel mixed firing sprayed with spraying nipple [23] burns from inlet channel [21], the further Thorough combustion of combustion chamber is evenly diffused into front open circles taper spreading speed reducer [24] through the cone end, and the high-temperature fuel gas group [25] that formation speed is relatively slow between taper spreading speed reducer [24] cone point and freeing pipe [13] is to ensure that combustion gas can not be extinguished, punching engine energy continuous firing.Inlet channel [21] can not share with turbofan by-pass air duct and directly enter afterburner with the 3rd duct, can jointly promote aircraft to accelerate sooner when firm startup punching engine with fanjet work simultaneously.Along with speed with highly improve constantly, inlet channel [21] can be reduced gradually, increase the speed of adjustable nozzle [2] ejection oxidizer, until close inlet channel [21] completely, adjustable nozzle [2] is opened just become rocket engine completely.

Cone gas diffuser [7] in Fig. 1, gas speed reducer [8], conical spreading speed reducer [19] in Fig. 3 and Fig. 4 and [24] are all hollow, cellular parallel with the combustion chamber breather pipe that inside has size adjustable, we can find out best tubaeform gas diffusion chamber [6] by theory calculate and experiment, hollow cone diffuser [7], the drift angle number of degrees of retarder [8] and spreading speed reducer [19] and [24], the size of height and the inside breather pipe and fuel oil atomizer [5], the various parameter such as position, ensure high-temperature fuel gas group [11] respectively, [20] and the speed of [25] no matter scramjet engine how soon have, all can not extinguish, ensure that punching engine can start with minimum speed, continual and steady efficient work.

Use the scheme in Fig. 3 and Fig. 4, only need spray in whirlpool, fanjet improves, do not need again the punching press/rocket engine in erection plan 1, the space no small weight of driving engine can reduced He occupy.

Fig. 5 is that scraggly sharkskin shape solid surface and fluid cliding friction analyze schematic diagram, why is scraggly sharkskin shape solid surface [27] less than the friction force of smooth solid surface? we will consider from molecule and atom angle, the molecule of solid or interatomic apart from little, application force large, the very little very difficult movement of elasticity, and the molecule of fluid and interatomic distance is large, application force is little and elasticity is comparatively large easily mobile.When sliding between fluid, protruding molecule or atom can flow away, and the place fallen in has fluid molecule, atom and automatically fills and leads up, and ensure that the sliding surface [26] between them is very level and smooth, thus friction force is just less.And the surface of solid is smooth again, also can not ensure that the molecule on surface or atom do not have convex-concave, when fluid slips over, this convex-concave more can not can not be filled and led up by automatic plastering when moving, and the friction force between them is just larger.When fluid molecule [25] slips on scraggly sharkskin shape solid surface [27] along sliding surface [26], the part that there is scraggly sharkskin shape solid surface [27] with regard to there being the fluid of respective thickness and shape and fall in, has just become the friction between the fluid that friction force is little and fluid between them.Shape and the degree of depth of sharkskin shape solid surface [27] are more reasonable, and sliding surface [26] is more level and smooth, and the friction force between them is less.Sharkskin shape solid surface [27] can also reduce the Aerodynamic Heating of hypersonic vehicle: friction force is little, frictional heat is just few, and exist high temperature air in sharkskin shape solid surface [27] can at any time substitute by the low air of outer surface temperature the effect reaching and cool.

The aerospace plane of this superelevation velocity of sound is designed to the wing of scalable, area and variable-angle, the speed along with aerospace plane increases and the minimizing of fuel, is inwardly shunk gradually by the wing of all stretching out, flies to adapt to it under the conditions such as different Mach number.Unmanned plane for superelevation velocity of sound can form formation, have man-machine lead commander under, can the low oil consumption of large area low-speed wing ground scout, monitor, patrol, motor-driven, the Small object of the weapon attacking low values such as self-contained guided missile is used to carry out air battle, when finding the general objective of high value, receiving and man-machinely just having started to accelerate, during speed unaccommodated to large area wing when assigning strike order, start explosive bolt by its jettisoning, the little wing simultaneously enabling applicable high-speed flight attacks this target.

Claims (1)

1. a hypersonic vehicle, it is characterized in that its punching press/rocket engine comprise variable geometry inlet Cai Yongjinqidaojihechicunkebianfangshi，Shi Boxihuo and with it by oxidizer adjustable nozzle [2], liquid oxygen or other oxidizer storage tanks [4] aircraft that oxidizer delivery duct [3] communicates be equipped with, fuel oil atomizer [5], tubaeform gas diffusion chamber [6], hollow cone gaseous diffuser [7], hollow cone gas speed reducer [8], combustion chamber [9] and adjustable nozzle [10], high velocity air forms the high temperature air mass [11] that a smooth combustion ensures punching engine continuous firing between hollow cone gaseous diffuser [7] and retarder [8], its turbine/ultra-combustion ramjet/rocket engine comprise variable geometry inlet Cai Yongjinqidaojihechicunkebianfangshi，Shi Boxihuo be modified as also can close completely and therein increase oxidizer adjustable nozzle [2], a combustion gas collecting chamber [16] and the suitable spout of length or freeing pipe [17] is increased after turbine, after the spraying nipple [18] of punching engine burns the fuel of atomization and the air mixed firing of coming in, the further Thorough combustion of combustion chamber is evenly diffused into front conical hollow spreading speed reducer [19] through the cone end, and a high-temperature fuel gas group [20] is formed to ensure that combustion gas can not be extinguished between taper spreading speed reducer [19] cone point and freeing pipe [17], punching engine energy continuous firing, until speed and just closed when being highly not suitable for whirlpool spray and be used alone punching engine, then by variable geometry inlet Cai Yongjinqidaojihechicunkebianfangshi，Shi Boxihuo by small size gradually to closing completely, adjustable nozzle [2] by little to opening completely, it has just become rocket engine, its turbofan/ultra-combustion ramjet/rocket engine is included in correct position between fan and afterburner increases the switch [22] that an inlet channel that can outwards open [21] and inwardly can close fanjet by-pass air duct, oxidizer adjustable nozzle [2] is established after inlet channel [21], when the maximum speed and height that it can arrive to be delivered to by aircraft by thrust type fanjet, open inlet channel [21], then the switch [22] of by-pass air duct and the triangle inlet channel [15] of fanjet is closed, this Airflow will be walked around fan and enter after the atomized fuel mixed firing sprayed with spraying nipple [23] burns from inlet channel [21], the further Thorough combustion of combustion chamber is evenly diffused into through the cone end preceding conical hollow spreading speed reducer [24], and a high-temperature fuel gas group [25] is formed to ensure that combustion gas can not be extinguished between taper spreading speed reducer [24] cone point and freeing pipe [13], punching engine energy continuous firing, along with speed with highly improve constantly, inlet channel [21] can be reduced gradually, increase the speed of adjustable nozzle [2] ejection oxidizer, until close inlet channel [21] completely, adjustable nozzle [2] is opened just become rocket engine completely, inlet channel [21] can not share with turbofan by-pass air duct and directly enter afterburner with the 3rd duct, aircraft is become the rough and uneven in surface sharkskin shape that friction force and Aerodynamic Heating are all little with the surface design of air high-speed friction.