Hypersonic aircraft resistance device

Abstract

The invention discloses a resistance device of a hypersonic aircraft. The resistance device comprises a resistance piece, a resistance device cabin, an ignition actuator, a limiting locking mechanism and the like, wherein the ignition actuator and the limiting locking mechanism are arranged in an inner cavity of the resistance device. The resistance sheet adopts a combined design of a curved surface structure and a crankshaft structure, and has a complete and smooth pneumatic shape in a folding state; the resistance sheet is fixed on the resistance device cabin body through the snapping pin, and after the fire actuator acts, the resistance sheet is unlocked and quickly opened; limiting pins, locking pins and springs of the limiting and locking mechanism are pressed in pin holes of the cabin body through resistance pieces, when the resistance pieces are unfolded, the two sets of locking pins are jacked into taper holes in the roots of the resistance pieces under the action of the springs, meanwhile, the limiting pins make contact with the wall of a U-shaped groove for limiting, and when the resistance pieces rebound, the locking pins completely enter the taper holes to complete locking. The technical problems of thermal protection, rapid opening, reliable locking and the like of the resistance device are solved, the installation manufacturability is good, and the falling speed control capacity of the hypersonic flight vehicle can be improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft, and in particular relates to a hypersonic aircraft resistance device. Background Art

[0002] The throwing type load condition has high requirements for the aircraft's falling speed and falling angle. The precise control of the aircraft's terminal falling speed and falling angle is often achieved by increasing the aircraft's drag area. In order to adapt to the different flight trajectory requirements of the aircraft, the drag area needs to be increased during the set period. This function is usually achieved by a drag device. In the early stage of the aircraft's flight, the drag device is closed to maintain low resistance. When it reaches the set trajectory position, the flight controller triggers the drag device driver, and the drag device is deployed to provide the required resistance.

[0003] In the past, drag devices were used on lower-speed aircraft, where the thermal environment was better and no thermal protection design was required. There were large adverse airflow steps on the surface of the drag devices, and the thermal environment of hypersonic aircraft was harsh, so the original plan could not be applied. In the past, the deployment drive of the drag device used elastic elements, and the spring energy density was limited, making it difficult to overcome the aerodynamic load under large dynamic pressure, and the deployment synchronization was greatly affected by the aerodynamic load.

[0004] Obviously, the existing resistance device solutions cannot adapt to the harsh thermal environment of hypersonic speed, overcome the aerodynamic drag under large dynamic pressure, and meet the requirements of short deployment time and good deployment synchronization. Summary of the invention

[0005] In order to overcome the shortcomings of the prior art, the present invention provides a hypersonic aircraft drag device, including a drag plate, a drag device cabin, and a pyrotechnic actuator placed in the inner cavity of the drag device, a limit locking mechanism, etc. The drag plate adopts a combined design of a curved surface structure and a crankshaft structure, and has a complete and smooth aerodynamic shape in a closed state; the drag plate is fixed to the drag device cabin by a break pin, and after the pyrotechnic actuator acts, its gunpowder gas pushes the drag plate to rotate and break the break pin, so that the drag plate is unlocked and quickly opened; the limit pin, the locking pin and the spring of the limit locking mechanism are pressed into the pin hole of the cabin by the drag plate, and when the drag plate is unfolded and close to being unfolded in place, the limit pin first pushes into the U-shaped groove at the root of the drag plate under the action of the spring, and when the drag plate is unfolded in place, two sets of locking pins push into the tapered hole at the root of the drag plate under the action of the spring, and at the same time, the limit pin contacts the wall of the U-shaped groove for limiting, and when the drag plate rebounds, the limit pin contacts the wall of the other side of the U-shaped groove to prevent rebound, and after this process, the locking pin completely enters the tapered hole to complete the locking. The present invention solves the technical problems of thermal protection, rapid opening and reliable locking of the resistance device, and has good installation processability, which can improve the falling speed control capability of the hypersonic aircraft.

[0006] The technical solution adopted by the present invention to solve the technical problem is as follows:

[0007] A hypersonic aircraft drag device, comprising a drag sheet, a drag device cabin, a pyrotechnic actuator and a limit locking mechanism; the drag device cabin comprises a drag device front cabin, a drag device middle cabin and a drag device rear cabin;

[0008] The resistance sheet includes a curved surface structure and a crankshaft structure; the crankshaft structure is fan-shaped and hollow, and is provided with a shaft hole, a U-shaped groove and two tapered holes; the resistance sheet is movably connected to the rear cabin of the resistance device through the shaft, and the front end of the resistance sheet is locked with the front cabin of the resistance device through a breaking pin, and when the resistance sheet is closed on the cabin of the resistance device, the outer surface forms a complete and smooth aerodynamic shape;

[0009] The fire actuator is placed inside the resistance device cabin and connected to the resistance device cabin by radial screws; after the fire actuator acts, the gas pushes the resistance plate to break the break pin, the resistance plate is unlocked and quickly opened, and the heat-proof plug constrains the break pin to prevent the mechanism from ejecting objects;

[0010] The limit locking mechanism includes a limit pin, a locking pin and a spring; the limit pin and the locking pin are placed in the pin hole of the rear cabin of the resistance device, and when the resistance sheet is closed, the limit pin and the locking pin are subject to the limiting compression spring of the crankshaft structure to store elastic force; when the resistance sheet is unfolded and almost in place, the limit pin is pushed into the U-shaped groove on the crankshaft structure under the action of the spring; when the resistance sheet is unfolded and in place, the locking pin is pushed into the tapered hole on the crankshaft structure under the action of the spring, and at the same time the limit pin contacts the wall of the U-shaped groove for limiting; when the resistance sheet rebounds, the limit pin contacts the wall on the other side of the U-shaped groove to prevent excessive rebound, and when it rebounds again, the locking pin completely enters the tapered hole to complete the locking.

[0011] Preferably, a heat-resistant coating is coated on the outer surface of the resistance device, and a heat-resistant plug is installed in the break pin hole.

[0012] Preferably, the thickness of the heat-resistant coating is designed to be 4 mm.

[0013] Preferably, the front cabin of the resistance device, the middle cabin of the resistance device, and the rear cabin of the resistance device are sequentially connected by radial screws to form a force transmission path of the resistance device.

[0014] Preferably, the pyrotechnic device is installed in the cabin of the resistance device by radial screws, and the internal piston is directly opposite to the reinforcement rib of the resistance sheet through a through hole on the cabin of the resistance device.

[0015] The beneficial effects of the present invention are as follows:

[0016] The present invention solves the technical problems of thermal protection, rapid opening and reliable locking of the resistance device, and has good installation processability, which can improve the falling speed control capability of the hypersonic aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1It is a schematic diagram of the folded structure of the resistance device of the present invention.

[0018] Figure 2 This is a schematic diagram of the structure of the resistance device of the present invention in a state of being unfolded at 28.5°.

[0019] Figure 3 It is a schematic diagram of the fully deployed state of the resistance device of the present invention (left view).

[0020] Figure 4 It is a schematic diagram (front view) of the resistance device of the present invention in a fully deployed state.

[0021] Figure numerals: 1—heat-proof coating, 2—front cabin of resistance device, 3—middle cabin of resistance device, 4—pull-off pin, 5—heat-proof plug, 6—resistance plate, 7—pyrotechnic device, 8—rear cabin of resistance device, 9—rotating shaft, 10—limit pin, 11—limit spring, 12—cover plate, 13—locking pin, 14—locking spring. DETAILED DESCRIPTION

[0022] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0023] The technical problem to be solved by the present invention is that the dynamic pressure of a hypersonic aircraft is large and the thermal environment is harsh during flight, and the resistance device has the characteristics of being able to withstand large thermal loads and not exceeding the thermal response limit before deployment, being able to overcome aerodynamic resistance under large dynamic pressure during deployment, and being able to reliably lock under atmospheric dynamic loads after deployment; at the same time, it meets the requirements of short deployment time, good deployment synchronization, and good assembly processability. In view of the problems existing in the prior art, the present invention provides a resistance device for hypersonic aircraft that can adapt to harsh thermal environments, withstand atmospheric dynamic loads, deploy quickly, have high synchronization, and be easy to assemble.

[0024] A hypersonic aircraft drag device proposed in the present invention is mainly composed of a drag plate, a drag device cabin, a pyrotechnic actuator and a limit locking mechanism.

[0025] The resistance plate is composed of a curved structure and a crankshaft structure. The crankshaft structure is fan-shaped and hollow. It is provided with a shaft hole, a U-shaped groove and two tapered holes. The resistance plate is movably connected with the rear cabin through a shaft. Its front end is locked with the front cabin through a break pin. When closed on the cabin, the outer surface forms a complete and smooth aerodynamic shape. A heat-resistant coating is applied on the outer surface of the resistance device, and a heat-resistant plug is installed in the break pin hole.

[0026] The fire actuator is placed inside the front cabin of the resistance device and is connected to the cabin by radial screws. After the fire actuator is activated, the gas pushes the resistance plate to break the break pin, the resistance plate is unlocked and opens quickly, and the heat-proof plug constrains the break pin to prevent the mechanism from ejecting objects.

[0027] The limit locking mechanism includes a limit pin, a locking pin and a spring. The limit pin and the locking pin are placed in the pin hole of the rear cabin. When the resistance plate is closed, the two pins are limited and compressed by the crankshaft structure to store elastic force by the spring. When the resistance plate is almost in place, the limit pin is pushed into the U-shaped groove on the crankshaft structure under the action of the spring. When the resistance plate is in place, the locking pin is pushed into the tapered hole on the crankshaft structure under the action of the spring. At the same time, the limit pin contacts the wall of the U-shaped groove for limiting. When the resistance plate rebounds, the limit pin contacts the wall on the other side of the U-shaped groove to prevent excessive rebound. When it rebounds again, the locking pin completely enters the tapered hole to complete the locking.

[0028] Example:

[0029] according to Figure 1 As shown, in a hypersonic aircraft resistance device of the present invention, the main structure is a three-part cabin body and four resistance plates. The unlocking power is provided by a pyrotechnic device, and the limit locking power is provided by an elastic energy storage element. The front cabin body 2 of the resistance device, the middle cabin body 3 of the resistance device, and the rear cabin body 8 of the resistance device are sequentially connected by radial screws to form a force transmission path of the resistance device. The resistance plate 6 is installed on the rear cabin body 8 of the resistance device through a rotating shaft 9. In the closed state, the outer surface forms a smooth aerodynamic shape with the outer surfaces of the front and rear cabins. It is fixed to the middle cabin body 3 of the resistance device by a breaking pin 4. In the open state, the inner surface faces the wind to provide flight resistance. The pyrotechnic device 7 is installed in the middle cabin body 3 of the resistance device by radial screws, and the internal piston is directly opposite to the resistance plate 6 reinforcement rib through the through hole on the middle cabin body 3 of the resistance device. There are 4 groups of through holes at the rear of the resistance device rear cabin 8, 3 through holes in each group are parallel, the middle hole is offset to the rear of the two side holes, the locking spring 10 and the locking pin 11 are installed in the two side holes, the limit spring 12 and the limit pin 13 are installed in the middle hole, and the limit locking mechanism is fixed to the rear cabin 8 of the resistance device through the cover plate 14 when the resistance sheet is closed, so that the spring is in a compressed state. The outer surface of the resistance device is coated with a heat-resistant coating 1, and the thickness is designed to be 4mm according to the flight environment. A molded high-silicon oxide heat-resistant plug 5 is installed in the pull-off pin hole to adapt to the flight thermal environment.

[0030] After the pyrotechnic device 7 is triggered, the combustion gas inside it pushes the piston to move outward, and the piston pushes the resistance plate 6 to break the break pin 4. The broken part of the break pin 4 is constrained in the hole by the heat-proof plug 5 to avoid flying out and colliding with other parts of the aircraft. The piston stops after moving 65mm, and the resistance plate 6 continues to rotate around the rotating shaft 9 under the action of inertia and aerodynamic force. When the U-shaped groove in the middle of the crankshaft structure reaches above the limit pin 13, the limit pin 13 is inserted into the U-shaped groove under the action of the limit spring 12. When the locking holes on both sides of the crankshaft structure reach above the locking pin 11, the locking pin 11 is inserted into the locking hole under the action of the locking spring 10. The resistance plate 6 rebounds after colliding with the rear cabin 8 of the resistance device. Due to the high rotation speed, the locking pin 11 is prone to not move into place. The resistance plate 6 rebounds to the limit pin 13 and collides with the U-shaped groove of the crankshaft structure, and then rebounds again. After rebounding several times, the locking pin 11 completely enters the locking hole to achieve locking.

Claims

1. A hypersonic vehicle drag device, characterized in that: It includes a resistance plate, a resistance device cabin, a fire actuator and a limit locking mechanism; the resistance device cabin includes a resistance device front cabin, a resistance device middle cabin and a resistance device rear cabin; The resistance sheet includes a curved surface structure and a crankshaft structure; the crankshaft structure is fan-shaped and hollow, and is provided with a shaft hole, a U-shaped groove and two tapered holes; the resistance sheet is movably connected to the rear cabin of the resistance device through the shaft, and the front end of the resistance sheet is locked with the front cabin of the resistance device through a breaking pin, and when the resistance sheet is closed on the cabin of the resistance device, the outer surface forms a complete and smooth aerodynamic shape; The fire actuator is placed inside the resistance device cabin and connected to the resistance device cabin by radial screws; after the fire actuator acts, the gas pushes the resistance plate to break the break pin, the resistance plate is unlocked and quickly opened, and the heat-proof plug constrains the break pin to prevent the mechanism from ejecting objects; The limit locking mechanism includes a limit pin, a locking pin and a spring; the limit pin and the locking pin are placed in the pin hole of the rear cabin of the resistance device, and when the resistance sheet is closed, the limit pin and the locking pin are subjected to the limiting compression spring of the crankshaft structure to store elastic force; when the resistance sheet is unfolded and almost in place, the limit pin is pushed into the U-shaped groove on the crankshaft structure under the action of the spring; when the resistance sheet is unfolded and in place, the locking pin is pushed into the tapered hole on the crankshaft structure under the action of the spring, and at the same time the limit pin contacts the wall of the U-shaped groove for limiting; when the resistance sheet rebounds, the limit pin contacts the wall on the other side of the U-shaped groove to prevent excessive rebound, and when it rebounds again, the locking pin completely enters the tapered hole to complete the locking.

2. A hypersonic vehicle drag device according to claim 1, characterized in that: The outer surface of the resistance device is coated with a heat-resistant coating, and a heat-resistant plug is installed in the break pin hole.

3. A hypersonic vehicle drag device according to claim 1, characterized in that: The thickness of the heat-resistant coating is designed to be 4 mm.

4. A hypersonic vehicle drag device according to claim 1, characterized in that: The front cabin of the resistance device, the middle cabin of the resistance device, and the rear cabin of the resistance device are sequentially connected by radial screws to form a force transmission path of the resistance device.

5. A hypersonic vehicle drag device according to claim 1, characterized in that: The pyrotechnic device is installed in the middle cabin of the resistance device through radial screws, and the internal piston is directly facing the resistance sheet reinforcement rib through the through hole on the middle cabin of the resistance device.

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