CN209905058U - Variable-geometry wide-speed-range hypersonic-velocity wave-rider aircraft - Google Patents
Variable-geometry wide-speed-range hypersonic-velocity wave-rider aircraft Download PDFInfo
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- CN209905058U CN209905058U CN201920681271.6U CN201920681271U CN209905058U CN 209905058 U CN209905058 U CN 209905058U CN 201920681271 U CN201920681271 U CN 201920681271U CN 209905058 U CN209905058 U CN 209905058U
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Abstract
A variable-geometry wide-speed-range hypersonic wave rider aircraft relates to a wave rider aircraft. The device is provided with a left movable wing, a right movable wing, a hydraulic control system, a wave-rider front body, a hydraulic control rod, a left hinge joint, a right hinge joint, a slide way, a machine body, a left strip wing and a right strip wing; the left movable wing and the right movable wing are respectively positioned at two ends of the fuselage, the left movable wing is fixedly connected with the left edge strip wing, the right movable wing is fixedly connected with the right edge strip wing, the hydraulic control system is integrally positioned in the middle of the fuselage, a hydraulic control rod is attached to the hydraulic control system, the hydraulic control rod extends out of the left end and the right end of the hydraulic control system, and the wave rider front body is arranged at the front end of the fuselage; the left hinged joint and the right hinged joint are respectively fixed on the left edge strip wing and the right edge strip wing, and the slideway is positioned below the hydraulic control system and is fixed in the machine body.
Description
Technical Field
The utility model relates to a take advantage of ripples body aircraft especially relates to and can realize high low latitude, high low-speed flight and independently fly and return wide-speed domain hypersonic speed of variable geometry of journey and take advantage of ripples body aircraft.
Background
The development of the adjacent space aircraft relates to national safety and peaceful space utilization, and is one of the focuses of the international competition for space-capturing technology at present. The pursuit of higher, faster, and more distant aircraft has been motivating aerospace researchers to make continuous efforts. The military and civil needs of the new century put forward higher-level requirements on aviation and aerospace. The traditional space shuttle is difficult to meet the requirements of all aerospace countries due to the factors of high launching and maintenance cost, poor reusability, complex system and the like. In order to meet the needs of military and civil in the new century, the concept of the wave carrier is developed, the wave carrier integrates the advantages of aviation and aerospace, becomes the development direction of aerospace technology in the future, draws high attention of aerospace major countries, and gradually develops research work. The flying speed of the waverider is extremely high, the front edge of the waverider has attached shock waves, the Ma number is about 5, and the waverider has the great advantages of low resistance, high lift force and large lift-drag ratio. After the 21 st century, as the design theory of the fuselage of the wave-rider configuration gradually matures and perfects, compared with the traditional aircraft, the hypersonic wave-rider aircraft has the unique pneumatic and structural advantages, and can meet the requirements of high lift-drag ratio and high integration during hypersonic cruise flight.
The good aerodynamic characteristics and the potential huge application prospect of the wave-rider aircraft. However, the existing wave-carrier aircraft cannot realize autonomous acceleration flight from the ground to high altitude supersonic speed, most of the wave-carrier aircraft need to be delivered to a preset height by a flight assisting rocket system and then separated to autonomously fly, hypersonic gliding flight in a near space is realized, processes such as aerodynamic force/heat, separation interference and the like are completed, and great fuel consumption and equipment cost exist in the process, and a great amount of labor and economic cost exists. One of the main reasons for this is that the wing area of a waverider aircraft is relatively small compared to conventional aircraft and it is difficult to provide sufficient lift at low flight speeds.
Disclosure of Invention
The utility model discloses an aim at to present to take advantage of the relative tradition aircraft of wave body aircraft wing area less, when flying speed is lower, be difficult to provide sufficient lift scheduling problem, provide and can realize high-low altitude, high-low speed flight and independently fly and return a variable geometric wide-speed domain hypersonic speed to take advantage of wave body aircraft of journey.
The utility model is provided with a left movable wing, a right movable wing, a hydraulic control system, a wave-rider front body, a hydraulic control rod, a left hinge joint, a right hinge joint, a slideway, a machine body, a left strip wing and a right strip wing;
the left movable wing and the right movable wing are respectively positioned at two ends of the fuselage, the left movable wing is fixedly connected with the left edge strip wing, the right movable wing is fixedly connected with the right edge strip wing, the hydraulic control system is integrally positioned in the middle of the fuselage, a hydraulic control rod is attached to the hydraulic control system, the hydraulic control rod extends out of the left end and the right end of the hydraulic control system, and the wave rider front body is arranged at the front end of the fuselage; the left hinged joint and the right hinged joint are respectively fixed on the left edge strip wing and the right edge strip wing, and the slideway is positioned below the hydraulic control system and is fixed in the machine body.
The below of hydraulic control system can be equipped with 4 pulleys, and 4 pulleys can be established in the track recess, drive hydraulic control system and remove in the track recess, are equipped with a supporting beam on the pulley, a supporting beam can be equipped with 2, and 2 pulleys are equipped with at the both ends of every supporting beam.
And electromagnetic sensors can be arranged at two ends of the slide way and used for correspondingly controlling the moving distance of the hydraulic control system, so that the moving error is avoided.
The utility model discloses reduced the use of rocket boosting system and fuel, will provide the advantage of independently flying for taking advantage of the rising of ripples body and increase flying speed when rising to a take the altitude.
The utility model has the following outstanding advantages:
the aircraft body is slightly improved, namely, a rotatable strake wing is designed and added, when the aircraft is in a low altitude, the strake wing is in an outward opening state, the effective wing area is increased, and the purpose is to provide larger lift force for the waverider aircraft to finish autonomous flight from the ground to the air, so that the use of a rocket boosting system can be reduced; when the waverider flies to a certain height, the waverider aircraft does not need high lift force to maintain the continuous rising of the waverider aircraft, and more of the requirement on the speed is high, at the moment, in order to reduce the resistance and improve the maneuvering characteristics, the strake wings can be retracted to the aircraft body through the hydraulic operation system by adjusting the opening degree of the strake wings, so that the strake wings with a part of area extend into the aircraft body, the effective wing area is reduced, and the purpose of supersonic speed or hypersonic speed flight is achieved.
On the operation of the side strip wing, the common machines such as a lever, a pulley, a gear and the like can be used as a power assisting mechanism at ordinary times. However, these mechanisms have two disadvantages: firstly, a little clearance is always left at various mechanical connection positions, and time delay is caused when force is transmitted; the second mechanical force transfer is direct, bi-directional, and if an obstruction is encountered during the transfer, it will often cause damage to the mechanism in the opposite direction. The hydraulic transmission power-assisted system is considered to be selected. During low-altitude takeoff, a pilot can open the edge wing of the wave rider only by operating the hydraulic booster, so that the high-altitude flight aircraft still has high lift force; meanwhile, when the aircraft reaches a certain height, a pilot still only needs to operate the hydraulic control system to retract the edge wings into the aircraft body so as to reduce the effective area of the aircraft body, and the flight speed and flight performance of the wave rider can be effectively improved. The position of a hydraulic control system is considered, hydraulic rods at two ends are respectively hinged on edge strips with rotatable two ends during design, the hydraulic control system is limited on a slideway, the hydraulic control system slides on the slideway along with the expansion and contraction of a control lever, and the slideway is fixed on the lower wall surface of the wave-rider aircraft, so that internal disorder can be effectively avoided.
Drawings
Fig. 1 is an outline view of the present invention when the wing of the wave-rider is retracted.
Fig. 2 is an external view of the wave-rider aircraft when the wings of the wave-rider aircraft of the present invention are opened to both sides by 4 °.
Fig. 3 is an outline view of the wave-rider aircraft of the present invention when the opening process of the wave-rider is up to 8 °.
Fig. 4 is a detailed view of the hydraulic operating system.
Detailed Description
The following examples will further illustrate the present invention with reference to the accompanying drawings.
Referring to fig. 1 to 4, the embodiment of the present invention is provided with a left movable wing 11, a right movable wing 12, a hydraulic control system 2, a wave-rider front body 3, a hydraulic control lever 4, a left hinge joint 51, a right hinge joint 52, a slide 6, a fuselage 7, a left edge wing 81, and a right edge wing 82;
the left movable wing 11 and the right movable wing 12 are respectively positioned at two ends of the fuselage 7, the left movable wing 11 is fixedly connected with the left strip wing 81, the right movable wing 12 is fixedly connected with the right strip wing 82, the hydraulic control system 2 is integrally positioned in the middle of the fuselage 7, a hydraulic control rod 4 is attached to the hydraulic control system 2, the hydraulic control rod 4 extends out of the left end and the right end of the hydraulic control system 2, and the wave rider precursor 3 is arranged at the front end of the fuselage 7; the left joint 51 and the right joint 52 are fixed on the left edge strip wing 81 and the right edge strip wing 82 respectively, and the slideway 6 is positioned below the hydraulic control system 2 and fixed inside the fuselage 7.
The below of hydraulic control system 2 is equipped with 4 pulleys 9, and 4 pulleys 9 are established in track recess 10, drive hydraulic control system 2 and remove in track recess 10, are equipped with a supporting beam 11 on the pulley 9, a supporting beam 11 can be equipped with 2, and 2 pulleys 9 are equipped with at the both ends of every supporting beam 11.
And electromagnetic sensors are arranged at two ends of the slide 6 and used for correspondingly controlling the moving distance of the hydraulic control system, so that moving errors are avoided.
In fig. 1, the point of rotation at which the wing opens, and the point at which the wing opens, is the top view of the strake when it is retracted into the fuselage, in which the internal operating mechanism is hidden from view so as to show it more clearly. As shown in the figure, the left movable wing 11 and the right movable wing 12 are located at two end positions of the fuselage 7, because the utility model discloses can adapt to different flight states through opening and retracting of aircraft wing, the left movable wing 11 and the right movable wing 12 will be opened and retracted together with the left side strip wing 81 and the right side strip wing 82 that tightly link firmly. The hydraulic control system 2 is integrally located in the middle of the fuselage 7, the hydraulic control system 2 is attached with the hydraulic control lever 4, the hydraulic control lever 4 extends out of the hydraulic control lever system 2 towards the left end and the right end, and is divided into two sections, one section close to the hydraulic control system 2 is slightly thicker, and one section close to the left hinged joint 51 and the right hinged joint 52 is thinner, so that the hydraulic control lever has a telescopic function, can extend into the slightly thicker section of the hydraulic control lever 4, and pushes the wings to open and contract. The left joint 51 and the right joint 52 are fixedly connected with the thin hydraulic control rod 4. The hydraulic control lever 4 is connected with the movable wing in a hinged mode, as shown in the figure, the requirement of opening and retracting of the wing is considered, so that the hydraulic control system 2 is placed on a slideway 6, namely the slideway 6 is positioned below the hydraulic control system 2, the slideway 6 is fixed in a fuselage 7, and electromagnetic sensors are arranged at two ends of the slideway 6 and used for correspondingly controlling the moving distance of the hydraulic control system, so that the moving error is avoided. The left and right strake wings 81 and 82 and the left and right movable wings 11 and 12 may be moved inward to an fuselage inner position.
In low-altitude flight, because a higher lift-drag ratio is needed, the hydraulic control system 2 is operated at the moment, so that the left movable wing 11 and the right movable wing 12 are outwards opened along the fuselage 7 and the slide way 6 under the action of the push rod 4 of the hydraulic system, wherein the position of the sliding central point is at a position A shown in figure 1, the state is the initial state of the utility model, by changing the structures of the fuselage 7, the left movable wing 11 and the right movable wing 12, under the action of the hydraulic control system 2, the hydraulic control rod 4 is extended, the hydraulic control system 2, the left strake wing 81 and the right strake wing 82 rotate around the sliding central point A to be outwards opened by 8 degrees, as shown in figure 3, the parts of the left strake wing 81 and the right strake wing 82, which extend into the fuselage 7, just extend out to be flush with the left and right boundaries of the fuselage 7, no redundant strake wings exist, and no excessive load, the purposes of improving lift-drag ratio and flying at low speed are achieved, and the structure cannot cause too large change, so that not only is the deformation cost greatly reduced, but also unnecessary waste of some fuel is reduced. The lift of the airplane is increased due to the slightly opened left edge strip wing 81 and right edge strip wing 82, and the operability and the maneuverability of the airplane are obviously improved when the airplane flies under low load.
When the speed reaches the sonic speed, in order to improve the flight performance of the waverider and achieve the requirement of higher speed, the structure needs to be changed, the hydraulic control rod 4 is shortened under the action of the hydraulic control system 2, the left movable wing 11 and the right movable wing 12 are pulled back to the fuselage 7 around the point A, namely the movable wings 11 and the right movable wing 12 on the two sides are respectively retracted by 8 degrees, after retraction, a part of the left edge strip wing 81 and the right edge strip wing 82 can be obviously seen to be hidden in the fuselage 7, and the speed can reach supersonic speed or ultrahigh sonic speed. As shown in fig. 1, it can be clearly seen that the sweep angle is changed while the wing area is effectively reduced, and the flying speed of the utility model can be obviously improved.
When returning to the ground, hydraulic control rod 4 extends, and the left movable wing 11 and the right movable wing 12 that link to each other with fuselage 7 will open 8 to both sides round A department respectively under hydraulic control system 2's effect, increase effective wing area, play the effect of speed reduction, make the utility model discloses quick deceleration in effectual time returns ground, as shown in fig. 3.
As described above, fig. 2 shows the state where the opening or contraction process of the left and right movable wings 11 and 12 and the left and right strake wings 81 and 82 is at 4 ° to the fuselage, in which the left and right strake wings 81 and 82 are portions extending into the fuselage 7, which are smaller than the regions shown by the left and right strake wings 81 and 82 in fig. 1, the effective areas of the left and right strake wings 81 and 82 are slightly larger than the effective areas of the left and right strake wings 81 and 82 in fig. 1.
Fig. 4 shows a detailed view of the hydraulic control system and the slide way, as shown in the figure, the slide way 6 has a limiting function, 4 pulleys 9 are arranged in the track groove 10, the pulleys 9 can move in the track groove 10 to drive the hydraulic control system 2 to move in the track groove 10, the pulleys 9 are provided with support beams 11, the support beams 11 are connected with the bottom of the hydraulic control system 2, as can be seen from the figure, the support beams 11 are provided with 2, and two ends of each support beam are provided with 2 pulleys 9.
The utility model mainly aims at the design of the hypersonic aircraft body and the edge wings and provides a larger lifting force when the low-altitude flying wings are unfolded; the edge wings shrink to reduce resistance in high-speed flight; the wide-speed-range flight with the ultrahigh sound speed of Mach number 5 from the ground to high altitude can be automatically completed, the flight aids and the fuel cost of the aircraft are greatly saved, the return difficulty of the aircraft is reduced, and the aerodynamic characteristics of high lift force and high lift-drag ratio of the waverider are still achieved. The utility model discloses not only make this take advantage of ripples body aircraft's flying height and flying speed all have a new change to look and promote, have good lift and hinder the characteristic to effectively reduce the use of some fuel resource relatively, improved the current situation of current take advantage of ripples body aircraft development greatly. The utility model discloses the development of china's hypersonic aircraft technique will be further promoted.
Claims (4)
1. A variable-geometry wide-speed-range hypersonic wave-rider aircraft is characterized by being provided with a left movable wing, a right movable wing, a hydraulic control system, a wave-rider front body, a hydraulic control rod, a left hinge joint, a right hinge joint, a slide way, an aircraft body, a left strip wing and a right strip wing;
the left movable wing and the right movable wing are respectively positioned at two ends of the fuselage, the left movable wing is fixedly connected with the left edge strip wing, the right movable wing is fixedly connected with the right edge strip wing, the hydraulic control system is integrally positioned in the middle of the fuselage, a hydraulic control rod is attached to the hydraulic control system, the hydraulic control rod extends out of the left end and the right end of the hydraulic control system, and the wave rider front body is arranged at the front end of the fuselage; the left hinged joint and the right hinged joint are respectively fixed on the left edge strip wing and the right edge strip wing, and the slideway is positioned below the hydraulic control system and is fixed in the machine body.
2. The variable geometry wide speed range hypersonic waverider aircraft according to claim 1, wherein 4 pulleys are provided below said hydraulic steering system, 4 pulleys being disposed in said track grooves for driving said hydraulic steering system to move in said track grooves.
3. The variable geometry wide speed range hypersonic waverider aircraft according to claim 2, wherein there are 2 support beams on said pulleys, and 2 pulleys are mounted on each support beam at each end.
4. The variable geometry wide velocity range hypersonic waverider aircraft of claim 1, wherein electromagnetic sensors are provided at each end of said runway.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201920681271.6U CN209905058U (en) | 2019-05-14 | 2019-05-14 | Variable-geometry wide-speed-range hypersonic-velocity wave-rider aircraft |
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| CN201920681271.6U CN209905058U (en) | 2019-05-14 | 2019-05-14 | Variable-geometry wide-speed-range hypersonic-velocity wave-rider aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110027704A (en) * | 2019-05-14 | 2019-07-19 | 厦门大学 | The fast domain Hypersonic waveriders aircraft of the width of variable-geometry and its design method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110027704A (en) * | 2019-05-14 | 2019-07-19 | 厦门大学 | The fast domain Hypersonic waveriders aircraft of the width of variable-geometry and its design method |
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