CN103939217A - Hypersonic variable-geometry air inlet channel with rectangular section, design method and work mode - Google Patents
Hypersonic variable-geometry air inlet channel with rectangular section, design method and work mode Download PDFInfo
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- CN103939217A CN103939217A CN201410156815.9A CN201410156815A CN103939217A CN 103939217 A CN103939217 A CN 103939217A CN 201410156815 A CN201410156815 A CN 201410156815A CN 103939217 A CN103939217 A CN 103939217A
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Abstract
The invention discloses a hypersonic variable-geometry air inlet channel with a rectangular section and belongs to the field of pneumatic design of aerospace aircrafts. A seam through which a lip mask adjustable side plate penetrates and moves is formed in the front body of an aircraft; one end of the lip mask adjustable side plate is linked with the leading edge of a lip mask with a rectangular section through a rotating motion pair and the other end of the lip mask adjustable side plate is connected with a side plate actuating barrel arranged in the front body of the aircraft; the side plate actuating barrel controls the lip mask adjustable side plate to rotate with single freedom degree. The invention further provides a design method and a work mode of the hypersonic variable-geometry air inlet channel with a rectangular section. By adjusting the sweep angle of the lip mask adjustable side plate, the adjustment of the air inlet channel from idle state to starting state and the increasing and decreasing of mach number flow rate capture rate of the air inlet channel are realized; the hypersonic variable-geometry air inlet channel with a rectangular section is simple in structure and easy to control; the work efficiency of the propulsion system of a suction type hypersonic aircraft is greatly increased.
Description
Technical field
The present invention relates to how much intake ducts of the hypersonic change in a kind of rectangular cross-section and design method and working method, belong to aerospace flight vehicle pneumatic design field.
Background technique
For hypersonic airbreather, the good aeroperformance of intake duct under design point can not guarantee that it all can normally stably work under the working state of all keys.Particularly for the hypersonic airbreather of wide range of Mach numbers work, when in non-design work state, can intake duct normal starting and be take less resistance and flow losses will be to evaluate the major criterion of intake duct synthetic aerodynamic performance as motor provides enough, meets the air mass flow that certain flow quality requires.
Intake duct becomes geometric techniques and refers to that modes such as utilizing intake duct self mechanical device or additive fluid, electromagnetism controls the working state of intake duct under different flight environment.For hypersonic airbreather, becoming the complexity of how much devices and controlling difficulty greatly to affect the working efficiency of aircraft.
At present, in the prior art of how much intake ducts of a large amount of changes that proposed, mostly only concentrate the problem that solves single aspect, as lower in low mach flow capture rate or intake duct is restarted problem, cannot solve the lower problem of restarting with intake duct of low mach flow capture rate by a set of geometry intake ducts that become simultaneously.
Summary of the invention
Technical problem to be solved by this invention is to overcome prior art defect, provides a kind of hypersonic inlet low mach flow that can simultaneously solve to catch how much intake ducts of the hypersonic change in rectangular cross-section not enough and that intake duct is restarted and design method and working method.
Working principle of the present invention is: on the hypersonic inlet architecture basics of traditional rectangular cross section, design and install the adjustable side plate of rotatable lip cover, according to the regime of flight of aircraft, regulate in real time lip cover side plate sweepback angle, help propulsion system to obtain best propulsive efficiency, be mainly used in air-inlet type hypersonic aircraft propulsion system.When intake duct causes intake duct to enter inoperative state because incoming flow Mach number is too low or firing chamber back-pressure is too high, the obvious characteristic in intake duct flow field is that airflow breakaway bag on a large scale appears in lip cover ingress, separated bag makes intake duct obstruction cause mass air flow to flow to intake duct outside, and its flow that flows into intake duct internal channel is less.In order to make intake duct starting, rotate the adjustable side plate of lip cover, increase the adjustable side plate of lip cover sweepback angle and make intake duct enter starting state by inoperative state; When intake duct starting normal work, as need increase intake duct Mach number traffic capture rate, reduce the adjustable side plate sweepback of lip cover angle; Otherwise as needed less intake duct Mach number traffic capture rate, increase the adjustable side plate sweepback of lip cover angle.
In order to solve the problems of the technologies described above, the invention provides how much intake ducts of the hypersonic change in a kind of rectangular cross-section, comprise aircraft precursor, rectangular cross-section lip cover, lip cover is adjustable side plate and side plate pressurized strut, described rectangular cross-section lip cover is fixed on aircraft precursor, described aircraft precursor is provided with cracking of passing and move for the adjustable side plate of lip cover, one end of the adjustable side plate of described lip cover links with the leading edge of rectangular cross-section lip cover by rotational motion is secondary, the other end through crack be arranged on aircraft precursor in side plate pressurized strut be connected, side plate pressurized strut is controlled the adjustable side plate single-degree-of-freedom of lip cover and is rotated.
In the present invention, the adjustable side plate of described lip cover is two sector structure lamellar bodies, is separately positioned on Chun Zhao both sides, rectangular cross-section, presses close to two madial walls of rectangular cross-section lip cover.
In the present invention, described aircraft precursor is binary wedge surface compression precursor, three-dimension curved surface compression precursor or waverider forebody derived.
In the present invention, under the prerequisite that does not affect the adjustable side plate motion of described lip cover, reduce the length and the width that crack as far as possible.
The present invention also provides a kind of rectangular cross-section the hypersonic design method that becomes how much intake ducts, specifically comprises the following steps:
1) lip cover reflected shock wave angle θ while, determining intake duct precursor shock wave sealing state according to aircraft inlet flow conditions
4;
2), according to lip cover reflected shock wave angle θ
4select lip cover fixed lateral plate back rake angle θ
3, described lip cover reflected shock wave angle θ
3be less than or equal to lip cover fixed lateral plate hypsokinesis angle θ
4;
3), according to lip cover fixed lateral plate back rake angle θ
3select rotatable lip cover side plate sweepback angle θ
2, described rotatable lip cover side plate sweepback angle θ
2be less than or equal to lip cover fixed lateral plate back rake angle θ
3;
4), by wind tunnel test or numerical simulation judgement intake duct, can under minimum work Mach number, start and normal work; If can, design completes; If can not, reselect lip cover reflected shock wave angle θ
4, repeat above-mentioned design procedure.
As preferentially, described step 2) lip cover fixed lateral plate back rake angle θ in
3than lip cover reflected shock wave angle θ
4little 1 °～2 °.
As preferentially, described step 3) rotatable lip cover side plate sweepback angle θ in
2than lip cover fixed lateral plate back rake angle θ
3little 1 °～2 °.
The working method that a kind of rectangular cross-section provided by the invention is hypersonic becomes how much intake ducts into:
When aircraft takes off from ground, lip cover is adjustable side plate sweepback angle θ
1for maximum value, lip cover is adjustable, and side plate is hidden in lip cover inside, rectangular cross-section completely;
When flying speed increases while approaching relay point Mach number flow gradually, lip cover is adjustable side plate sweepback angle θ
1for maximum value, lip cover is adjustable, and side plate is hidden in lip cover inside, rectangular cross-section completely;
When flying speed reaches relay point Mach number, lip cover is adjustable side plate sweepback angle θ
1for reducing gradually, lip cover is adjustable side plate rotates and to rectangular cross-section lip cover external expansion;
When aircraft speed is further increased in flying speed in limited time, lip cover is adjustable side plate sweepback angle θ
1be decreased to minimum value, lip cover is adjustable, and side plate turns to the outside maximum position of rectangular cross-section lip cover;
When decline too low or firing chamber back-pressure of flying speed, uprush while causing intake duct inoperative, lip cover is adjustable side plate sweepback angle θ
1increase fast, until the disappearance of Chun Zhao ingress, rectangular cross-section airflow breakaway bag, intake duct starting.
Beneficial effect of the present invention is: (1), by rotation, adjust the adjustable side plate of lip cover sweepback angle θ
1, realize intake duct by inoperative state to the adjusting that enters starting state, after intake duct starting is normal, according to propulsion system, the demand of air mass flow is adjusted to the adjustable side plate of lip cover sweepback angle θ
1can conveniently increase or reduce intake duct Mach number traffic capture rate, it has been realized catching with air flue of intake duct Mach number flow simultaneously and has started; (2), it is simple in structure in the present invention, it is convenient to control, and greatly improves the working efficiency of air-inlet type hypersonic aircraft propulsion system.
Accompanying drawing explanation
Fig. 1 is how much intake duct structural representations of the hypersonic change in rectangular cross-section of the present invention;
Fig. 2 is the adjustable side plate of lip cover and side plate pressurized strut schematic diagram;
Fig. 3 is intake duct precursor shock wave of the present invention and lip cover reflected shock wave front view;
Fig. 4 is how much Design of Inlet flow charts of the hypersonic change in rectangular cross-section of the present invention;
Fig. 5 is how much intake duct working method explanatory drawings of the hypersonic change in rectangular cross-section of the present invention.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
As shown in Figure 1, how much intake ducts of the hypersonic change in rectangular cross-section of the present invention, comprise hypersonic aircraft precursor 1, lip cover is adjustable side plate 2, rectangular cross-section lip cover 3 and side plate pressurized strut 4; The precursor of hypersonic flight shown in Fig. 11 is rough schematic view, and concrete form can be a kind of in the classifications such as binary wedge surface in traditional hypersonic inlet compression precursor, three-dimension curved surface compression precursor and waverider forebody derived.Rectangular cross-section lip cover 3 is fixedly mounted on the top of hypersonic aircraft precursor 1, and two side plate pressurized strut 4 symmetries are fixedly mounted in hypersonic aircraft precursor 1, and its start instruction is from flight control system or propulsion system controller.On hypersonic aircraft precursor 1, have and crack with the movement interference place of the adjustable side plate 2 of lip cover, for the adjustable side plate 2 of lip cover, pass and move; Its cracking length is determined by adjustable side plate 4 thickness of lip cover by the adjustable side plate 2 moving region size decisions of lip cover, the width that cracks, reduces length and the width of seam under the prerequisite that does not affect the adjustable side plate motion of lip cover as far as possible.Lip cover is adjustable, and side plate 2 is two symmetrical sector structure lamellar bodies, be separately positioned on the both sides of rectangular cross-section lip cover 3, its one end is connected to the leading edge of rectangular cross-section lip cover 3 by a pair of rotational motion pair, on-link mode (OLM) can be hinged or riveted joint etc., and during link, rotational motion pair should retain the leading edge shape of rectangular cross-section lip cover 3 to greatest extent; Two sector structure lamellar bodies are pressed close to respectively rectangular cross-section lip cover 3 interior both sides sidewalls, when the adjustable side plate of lip cover 2 rotates, still keep pressing close to rectangular cross-section lip cover 3 madial walls, under the prerequisite of not disturbing the adjustable side plate 2 of lip cover to rotate, reduce distance between the adjustable side plate 2 of lip cover and rectangular cross-section lip cover 3 madial walls to avoid flow leakage as far as possible; The other end of two symmetrical sector structure lamellar bodies is connected with two side plate pressurized struts 4 respectively through cracking of hypersonic aircraft precursor 1 respectively, and the adjustable side plate 4 of lip cover that two symmetrical sector structure lamellar bodies are controlled respectively in two side plate pressurized struts 4 carries out single-degree-of-freedom rotation.
How much intake ducts of the hypersonic change in rectangular cross-section of the present invention are consistent with the aerodynamic performance of conventional hypersonic inlet under design point, and lip cover is adjustable, and come the aerodynamic performance impact of stream mode under intake duct minimum on design adding of side plate 2.
As shown in Figure 2, lip cover is adjustable side plate 2 is controlled and is rotated by side plate pressurized strut 4, and side plate pressurized strut 4 in the drawings level is stretched out left, lip cover is adjustable side plate sweepback angle θ
1reduce; Side plate pressurized strut 4 in the drawings level is shunk to the right, lip cover is adjustable side plate sweepback angle θ
1increase, side plate pressurized strut 4 control commands are from flight control system or propulsion system controller.
As shown in Figure 3,4, how much Design of Inlet method detailed processes of the hypersonic change of rectangular cross-section of the present invention entrance into:
Lip cover reflected shock wave angle θ while first, determining intake duct precursor shock wave 5 sealing state according to aircraft inlet flow conditions
4;
Secondly, according to lip cover reflected shock wave angle θ
4select lip cover fixed lateral plate back rake angle θ
3, determine that principle is: lip cover fixed lateral plate back rake angle θ
3≤ lip cover reflected shock wave angle θ
4; Preferred lip cover fixed lateral plate back rake angle θ
3than lip cover reflected shock wave angle θ
4little 1 °～2 °;
Then, according to lip cover fixed lateral plate back rake angle θ
3select rotatable lip cover side plate sweepback angle θ
2, determine that principle is: rotatable lip cover side plate sweepback angle θ
2≤ lip cover fixed lateral plate back rake angle θ
3; Preferably rotatable lip cover side plate sweepback angle θ
2than lip cover fixed lateral plate back rake angle θ
3little 1 °～2 °;
Finally, by wind tunnel test or numerical simulation judgement intake duct, can under minimum work Mach number, start and normal work.If can, design completes; If can not, reselect lip cover reflected shock wave angle θ
4, repeat above-mentioned design procedure.
As shown in Figure 5, how much intake duct working methods of the hypersonic change of rectangular cross-section of the present invention entrance comprise following process:
When aircraft takes off from ground, lip cover is adjustable side plate sweepback angle θ
1for maximum value, adjustable side plate is hidden in lip cover 3 inside, rectangular cross-section completely;
When flying speed increases while approaching relay point Mach number gradually, lip cover is adjustable side plate sweepback angle θ
1for maximum value, lip cover is adjustable, and side plate 2 is hidden in lip cover 3 inside, rectangular cross-section completely;
When flying speed reaches relay point Mach number, lip cover is adjustable side plate sweepback angle θ
1for reducing gradually, lip cover is adjustable side plate 2 rotates and to rectangular cross-section lip cover 3 external expansions;
When aircraft speed is further increased in flying speed in limited time, lip cover is adjustable side plate sweepback angle θ
1be decreased to minimum value, lip cover is adjustable, and side plate 2 turns to rectangular cross-section lip cover 3 outside maximum positions;
When decline too low or firing chamber back-pressure of flying speed, uprush while causing intake duct inoperative, lip cover is adjustable side plate sweepback angle θ
1increase fast, lip cover is adjustable, and side plate 2 rotates and to rectangular cross-section lip cover 3 internal contraction, until lip cover 3 ingress airflow breakaway bags in rectangular cross-section disappear, and intake duct starting.
The above is only the preferred embodiment of the present invention, it should be pointed out that for those skilled in the art, can also make some improvement under the premise without departing from the principles of the invention, and these improvement also should be considered as protection scope of the present invention.
Claims (8)
1. how much intake ducts of the hypersonic change in a rectangular cross-section, comprise aircraft precursor (1) and rectangular cross-section lip cover (3), described rectangular cross-section lip cover (3) is fixed on aircraft precursor (1), it is characterized in that: also comprise the adjustable side plate of lip cover (2) and side plate pressurized strut (4), described aircraft precursor (1) is provided with cracking of passing and move for the adjustable side plate of lip cover (2), one end of the adjustable side plate of described lip cover (2) links with the leading edge of rectangular cross-section lip cover (3) by rotational motion is secondary, the other end is connected through the side plate pressurized strut (4) interior with being arranged on aircraft precursor (1) of cracking, side plate pressurized strut (4) is controlled the adjustable side plate of lip cover (2) single-degree-of-freedom and is rotated.
2. how much intake ducts of the hypersonic change in rectangular cross-section according to claim 1, it is characterized in that: the adjustable side plate of described lip cover (2) is two sector structure lamellar bodies, be separately positioned on the both sides of rectangular cross-section lip cover (3), press close to two madial walls of rectangular cross-section lip cover (3).
3. how much intake ducts of the hypersonic change in rectangular cross-section according to claim 1, is characterized in that: described aircraft precursor (1) is binary wedge surface compression precursor, three-dimension curved surface compression precursor or waverider forebody derived.
4. how much intake ducts of the hypersonic change in rectangular cross-section according to claim 1, is characterized in that: under the prerequisite that does not affect the adjustable side plate of described lip cover (2) motion, reduce the length and the width that crack as far as possible.
5. according to the hypersonic design method that becomes how much intake ducts in the rectangular cross-section described in claim 1 to 4 any one, it is characterized in that comprising the following steps:
1) lip cover reflected shock wave angle θ 4 while, determining intake duct precursor shock wave sealing state according to aircraft inlet flow conditions;
2), according to lip cover reflected shock wave angle θ 4, select lip cover fixed lateral plate back rake angle θ 3, described lip cover reflected shock wave angle θ 3 is less than or equal to lip cover fixed lateral plate hypsokinesis angle θ 4;
3), according to lip cover fixed lateral plate back rake angle θ 3, select rotatable lip cover side plate sweepback angle θ 2, described rotatable lip cover side plate sweepback angle θ 2 is less than or equal to lip cover fixed lateral plate back rake angle θ 3;
4), by wind tunnel test or numerical simulation judgement intake duct, can under minimum work Mach number, start and normal work; If can, design completes; If can not, reselect lip cover reflected shock wave angle θ 4, repeat above-mentioned design procedure.
6. the hypersonic design method that becomes how much intake ducts in rectangular cross-section according to claim 5, is characterized in that: described step 2) lip cover fixed lateral plate back rake angle θ 3 than lip cover reflected shock wave angle θ 4 little 1 °～2 °.
7. the hypersonic design method that becomes how much intake ducts in rectangular cross-section according to claim 5, is characterized in that: described step 3) rotatable lip cover side plate sweepback angle θ 2 than lip cover fixed lateral plate back rake angle θ 3 little 1 °～2 °.
8. according to the hypersonic working method that becomes how much intake ducts in the rectangular cross-section described in claim 1 to 4 any one, it is characterized in that:
When aircraft takes off from ground, lip cover is adjustable, and side plate sweepback angle θ 1 is maximum value, and lip cover is adjustable, and side plate is hidden in lip cover inside, rectangular cross-section completely;
When flying speed increases while approaching relay point Mach number flow gradually, lip cover is adjustable, and side plate sweepback angle θ 1 is maximum value, and lip cover is adjustable, and that side plate is hidden in rectangular cross-section lip cover is completely inner;
When flying speed reaches relay point Mach number, lip cover is adjustable side plate sweepback angle θ 1 is for reducing gradually, and lip cover is adjustable, and side plate rotates and to rectangular cross-section lip cover external expansion;
When aircraft speed is further increased in flying speed, prescribe a time limit, lip cover is adjustable, and side plate sweepback angle θ 1 is decreased to minimum value, and lip cover is adjustable, and side plate turns to the outside maximum position of rectangular cross-section lip cover;
When decline too low or firing chamber back-pressure of flying speed, uprush while causing intake duct inoperative, lip cover is adjustable, and side plate sweepback angle θ 1 increases fast, until the disappearance of Chun Zhao ingress, rectangular cross-section airflow breakaway bag, intake duct starting.
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