Integrated airfoil and rotating vane type pyrotechnic actuator thereof

Abstract

The invention discloses an integrated airfoil and a rotating vane type pyrotechnic actuator thereof, the rotating vane type pyrotechnic actuator is used for unfolding a folding airfoil of an aircraft, and fuel gas generated after gunpowder combustion is used for directly driving a rotor fixedly connected with the airfoil to rotate, so that rotating displacement is directly output and the airfoil is driven to be unfolded. According to the pyrotechnic actuator, fuel gas generated after gunpowder combustion is directly adopted to drive the rotor to rotate, the rotor drives the airfoils to rotate, an intermediate conversion mechanism is omitted, the transmission efficiency is improved, and the structure is simplified.

Description

Technical Field

[0001] The invention belongs to the technical field of mechanical transmission, and in particular relates to an integrated wing surface and a rotary blade type fire actuator thereof. Background Art

[0002] In order to facilitate transportation, ejection and boosted takeoff, the wing surface of the aircraft must adopt a folding structure. By folding its wing surface, it can be installed in a launch box or an embedded structure. When the aircraft is ejected and boosted to the designed altitude, its wing surface must be unfolded. Because the aircraft will be subjected to huge and complex aerodynamic loads during the boost phase, unfolding the wing surface requires a large unfolding torque. Existing wing surface unfolding mechanisms must convert linear drive into rotational drive, resulting in low transmission efficiency. Summary of the invention

[0003] In order to solve the technical problem of rapid deployment under heavy load, the present invention provides an integrated airfoil and its rotating blade pyrotechnic actuator. The pyrotechnic actuator directly uses the combustion gas generated by the combustion of gunpowder to drive the rotor to rotate, and drives the airfoil to rotate through the rotor, eliminating the intermediate conversion mechanism, improving the transmission efficiency and simplifying the structure.

[0004] In order to achieve the above object, the present invention adopts the following specific technical solutions:

[0005] The present invention provides a rotary blade pyrotechnic actuator for unfolding the folded wing surface of an aircraft. The pyrotechnic actuator utilizes the combustion gas generated by the combustion of gunpowder to directly drive the rotor fixedly connected to the wing surface to rotate, thereby directly outputting the rotational displacement and driving the wing surface to unfold.

[0006] Furthermore, it includes a cylinder, a rotor, a stator blade, a rotor blade, gunpowder and an electric ignition device;

[0007] The rotor is rotatably mounted in the inner hole of the cylinder and is coaxially arranged with the inner hole;

[0008] The stator blades are fixedly mounted on the inner hole wall of the cylinder and are sealed with the rotor;

[0009] The rotor blades are fixedly mounted on the outer wall of the rotor and are in sealing cooperation with the cylinder;

[0010] The cylinder body is processed with a deflagration chamber and a throat; the throat is located between the stator blades and the rotor blades, and connects the deflagration chamber with the inner hole of the cylinder body;

[0011] The gunpowder is contained in the deflagration chamber and is used for burning to generate high-temperature and high-pressure gas;

[0012] The electric ignition device is fixedly mounted on the outer end of the deflagration chamber and is used to ignite the gunpowder.

[0013] Furthermore, the cylinder is processed with a threaded interface at the outer end of the deflagration chamber;

[0014] The electric ignition tool is threadedly connected to the threaded interface.

[0015] Furthermore, a first sealing structure is provided on a side of the stator blade facing the rotor;

[0016] The first sealing structure is used to seal a gap between the stator blade and the rotor.

[0017] Furthermore, a second sealing structure is provided on a side of the rotor blade facing the cylinder;

[0018] The second sealing structure is used to seal the gap between the rotor blades and the inner barrel;

[0019] The throat is located between the first sealing structure and the second sealing structure.

[0020] Furthermore, the stator blade is provided with a first sealing groove on a side facing the rotor;

[0021] The rotor blade is provided with a second sealing groove on a side facing the cylinder;

[0022] The first sealing structure is composed of a first sealing strip installed in the first sealing groove;

[0023] The second sealing structure is composed of a second sealing strip installed in the second sealing groove.

[0024] In addition, the present invention also provides an integrated airfoil, which includes an airfoil and the rotary blade type pyrotechnic actuator in the above technical solution;

[0025] The barrel of the rotary blade type fire working actuator forms a wing root / inner wing;

[0026] The rotor of the rotary vane type pyrotechnic actuator is fixedly connected to the airfoil.

[0027] Furthermore, the airfoil is constituted by an outer wing.

[0028] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0029] 1. The rotary blade pyrotechnic actuator of the present invention realizes a rotary blade pyrotechnic actuator technology for the first time. Compared with the existing airfoil unfolding mechanism which must convert the linear drive into the rotary drive, the rotary blade pyrotechnic actuator of the present invention uses the gunpowder gas to directly drive the rotor fixedly connected to the airfoil to rotate and directly output the angular displacement and torque. Therefore, the rotary blade pyrotechnic actuator does not have a conversion mechanism and has a high transmission efficiency.

[0030] 2. The rotary blade type pyrotechnic actuator of the present invention has the inherent advantage of integration. The wing root is formed by a cylinder and the rotor and the wing surface are fixedly connected to form an integrated wing surface. The integrated wing surface has the technical advantages of simple structure and safety and reliability. It reduces the manufacturing cost of the folding wings and is easy to mass produce.

[0031] 3. Compared with existing products, the rotary blade pyrotechnic actuator of the present invention sets the throat between the stator blades and the rotor blades, requires less gunpowder loading, has a lower working pressure, and its reliability and safety will be effectively improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a structural schematic diagram of the rotary blade type fire working actuator of the present invention;

[0033] Figure 2 Schematic diagram of the structure of the integrated wing.

[0034] Among them, 1-cylinder, 2-rotor, 3-stator blades, 4-rotor blades, 5-throat, 6-gunpowder, 7-electric ignition device, 8-outer wing, 9-wing root. DETAILED DESCRIPTION

[0035] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0036] Because the aircraft will be subjected to huge and complex aerodynamic loads during the boost phase, a large deployment torque is required to deploy the wing surface. In order to solve the problem of rapid deployment under large loads, the present invention provides a rotary blade pyrotechnic actuator. Since the pyrotechnic actuator eliminates the intermediate conversion mechanism, improves the transmission efficiency and simplifies the structure, the pyrotechnic actuator of the present invention has the characteristics of low working pressure and high reliability. At the same time, the structure of the pyrotechnic actuator of the present invention also has the inherent integrated technical advantage, which will fill the gap in the wing surface integration technology of the aircraft.

[0037] Embodiment 1

[0038] The embodiment of the present invention provides a rotary blade pyrotechnic actuator, which is used to unfold the folded wing surface of an aircraft. The working principle of the rotary blade pyrotechnic actuator is as follows: the gas generated by the gunpowder 6 directly drives the rotor 2 fixedly connected to the wing surface to rotate, thereby directly outputting the rotational displacement and driving the wing surface to unfold. The specific structure of the rotary blade pyrotechnic actuator is as follows:

[0039] like Figure 1 As shown, the rotary vane pyrotechnic actuator includes a cylinder 1, a rotor 2, stator blades 3, rotor blades 4, gunpowder 6 and an electric ignition device 7.

[0040] The cylinder 1 is provided with an inner hole, which serves as a rotating chamber of the rotor 2; the cylinder 1 is fixedly connected to the aircraft body to provide an installation basis; the rotor 2 can be rotatably installed in the inner hole of the cylinder 1 and is coaxially arranged with the inner hole of the cylinder 1; the rotor 2 is a cylindrical structure.

[0041] The stator blades 3 are fixedly mounted on the inner hole wall of the cylinder 1 and are sealed with the rotor 2; the inner hole wall of the cylinder 1 is provided with a groove for mounting the stator blades 3, a part of the stator blades 3 is fixedly mounted in the groove, and the other part of the stator blades 3 protrudes from the groove and is sealed with the rotor 2.

[0042] The rotor blades 4 are fixedly mounted on the outer wall of the rotor 2 and are sealed with the cylinder 1. Similarly, a groove is provided on the outer wall of the rotor 2. A part of the rotor blades 4 is fixedly mounted in the groove of the outer wall of the rotor 2, and the other part protrudes from the outside of the groove of the rotor 2 and is sealed with the cylinder 1.

[0043] The cylinder 1 is processed with a deflagration chamber and a throat 5; the throat 5 is located between the stator blades 3 and the rotor blades 4, and connects the deflagration chamber with the inner hole of the cylinder 1; the gunpowder 6 is contained in the deflagration chamber, and is used to burn and produce high-temperature and high-pressure gas; the gunpowder 6 can be in the form of electrical excitation, etc.; the electric ignition tool 7 is fixedly installed at the outer end of the deflagration chamber, and is used to ignite the gunpowder 6. The cylinder 1 is processed with a threaded interface at the outer end of the deflagration chamber; the electric ignition tool 7 is connected to the threaded interface by threads, and the threaded connection facilitates the installation of the electric ignition tool 7.

[0044] In order to improve the actuation effect of gas, Figure 1 and Figure 2As shown, a first sealing structure is provided on the side of the stator blade 3 facing the rotor 2; the first sealing structure is used to seal the gap between the stator blade 3 and the rotor 2; at the same time, a second sealing structure is provided on the side of the rotor blade 4 facing the cylinder 1; the second sealing structure is used to seal the gap between the rotor blade 4 and the inner cylinder; the throat 5 is located between the first sealing structure and the second sealing structure, and when the gunpowder 6 is ignited, the high-temperature and high-pressure gas enters the space surrounded by the outer wall of the rotor 2, the inner wall of the cylinder 1, the first sealing structure, the second sealing structure, the rotor blade 4 and the stator blade 3 through the throat 5. At the same time, since the cylinder 1 is fixed, the rotor blade 4 rotates driven by the gas, thereby driving the rotor 2 to rotate.

[0045] like Figure 1 and Figure 2 As shown, the stator blade 3 is provided with a first sealing groove on the side facing the rotor 2; the rotor blade 4 is provided with a second sealing groove on the side facing the cylinder 1; the first sealing structure is composed of a first sealing strip installed in the first sealing groove; the second sealing structure is composed of a second sealing strip installed in the second sealing groove.

[0046] The working principle of the above-mentioned rotary blade type fire-actuated actuator is as follows: the gunpowder 6 starts to burn after being ignited by the electric igniter 7. The gunpowder 6 burns rapidly in the deflagration chamber to produce high-temperature and high-pressure gas. The gas enters the inner hole of the cylinder 1 through the throat 5. The gas pressure rises rapidly and acts on the stator blades 3 and the rotor blades 4. Since the stator blades 3 are fixed on the cylinder 1 and the rotor blades 4 are fixed on the rotor 2, the gas pressure will directly drive the rotor 2 to rotate. The rotor 2 serves as the output shaft of the fire-actuated actuator, so the fire-actuated actuator of the present invention can directly output the rotational displacement.

[0047] The above-mentioned rotary blade pyrotechnic actuator uses the high-temperature and high-pressure gas generated by the gunpowder 6 to directly drive the rotor 2 fixedly connected to the wing surface to rotate, and directly outputs angular displacement and torque through the rotor 2, thereby realizing the rotary blade pyrotechnic actuator for the first time. Compared with the existing wing surface deployment mechanism that must convert linear drive into rotational drive, the above-mentioned rotary blade pyrotechnic actuator does not have a motion conversion mechanism, and its transmission efficiency is high and the structure is simple.

[0048] At the same time, compared with the existing wing deployment mechanism, it requires less gunpowder loading and has a lower working pressure, and its reliability and safety will be effectively improved.

[0049] The above-mentioned rotary blade pyrotechnic actuator also has the inherent advantage of integration. The wing root 9 is formed by the cylinder 1 and fixedly installed on the aircraft, and the rotor 2 is fixedly connected to the wing surface to form an integrated wing surface. The integrated wing surface has the technical advantages of simple structure and safety and reliability, which reduces the manufacturing cost of the folding wings and is easy to mass produce.

[0050] Embodiment 2

[0051] An embodiment of the present invention provides an integrated airfoil, such as Figure 2 As shown, the integrated airfoil includes the airfoil and the rotary vane pyrotechnic actuator in the above embodiment; the rotary vane pyrotechnic actuator uses the combustion gas generated by the gunpowder 6 to directly drive the rotor 2 fixedly connected to the airfoil to rotate, thereby directly outputting the rotational displacement and driving the airfoil to unfold; the integrated airfoil can be realized by the airfoil, the cylinder 1, the rotor 2, the stator blades 3, the rotor blades 4, the gunpowder 6 and the electric ignition device 7. The cylinder 1 of the rotary vane pyrotechnic actuator forms the wing root 9 / inner wing and is fixedly connected to the aircraft body; the airfoil is composed of the outer wing 8; the rotor 2 of the rotary vane pyrotechnic actuator is fixedly connected to the airfoil, and the airfoil is unfolded from the folded state by driving the outer wing 8 to rotate relative to the aircraft body through the rotor 2.

[0052] The working principle of the above-mentioned integrated airfoil is the same as that of the rotary blade pyrotechnic actuator. The electric ignition device 7 is installed on the wing root 9 / inner wing, and the gunpowder 6 is installed in the deflagration chamber in the wing root 9 / inner wing. First, the electric ignition device 7 ignites the gunpowder 6, which burns rapidly and produces a large amount of high-temperature and high-pressure gas in the deflagration chamber. The gas enters the power chamber through the throat 5. The power chamber is formed by the inner hole wall of the cylinder 1, the stator blades 3, the outer wall of the rotor 2, and the rotor blades 4. Because the stator blades 3 are fixed on the inner wing / wing root 9, and the rotor blades 4 are fixed on the rotor 2, the gas pressure will directly drive the rotor 2 to rotate. Because the rotor 2 and the outer wing 8 are fixedly connected as a whole, the rotor 2 drives the airfoil to rotate and unfold while rotating. After unfolding in place, the outer wing 8 and the inner wing are locked as a whole by the locking mechanism.

[0053] Obviously, those skilled in the art can make various changes and modifications to the embodiments of the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A rotary blade pyrotechnic actuator for unfolding a folding wing surface of an aircraft, characterized in that: The pyrotechnic actuator utilizes the combustion gas generated by the combustion of gunpowder to directly drive the rotor fixedly connected to the airfoil to rotate, thereby directly outputting the rotational displacement and driving the airfoil to unfold.

2. The rotary vane fire actuator according to claim 1, characterized in that: It includes a cylinder, a rotor, stator blades, rotor blades, gunpowder and an electric ignition device; The rotor is rotatably mounted in the inner hole of the cylinder and is coaxially arranged with the inner hole; The stator blades are fixedly mounted on the inner hole wall of the cylinder and are sealed with the rotor; The rotor blades are fixedly mounted on the outer wall of the rotor and are in sealing cooperation with the cylinder; The cylinder body is processed with a deflagration chamber and a throat; the throat is located between the stator blades and the rotor blades, and connects the deflagration chamber with the inner hole of the cylinder body; The gunpowder is contained in the deflagration chamber and is used for burning to generate high-temperature and high-pressure gas; The electric ignition device is fixedly mounted on the outer end of the deflagration chamber and is used to ignite the gunpowder.

3. The rotary vane fire actuator according to claim 2, characterized in that: The cylinder is processed with a threaded interface at the outer end of the deflagration chamber; The electric ignition tool is threadedly connected to the threaded interface.

4. The rotary vane fire actuator according to claim 2 or 3, characterized in that: A first sealing structure is provided on a side of the stator blade facing the rotor; The first sealing structure is used to seal a gap between the stator blade and the rotor.

5. The rotary vane fire actuator according to claim 4, characterized in that: A second sealing structure is provided on the side of the rotor blade facing the cylinder; The second sealing structure is used to seal the gap between the rotor blades and the inner barrel; The throat is located between the first sealing structure and the second sealing structure.

6. The rotary vane fire actuator according to claim 5, characterized in that: The stator blade is provided with a first sealing groove on a side facing the rotor; The rotor blade is provided with a second sealing groove on a side facing the cylinder; The first sealing structure is composed of a first sealing strip installed in the first sealing groove; The second sealing structure is composed of a second sealing strip installed in the second sealing groove.

7. An integrated airfoil, characterized in that: A rotary vane fire actuator comprising an airfoil and a rotary vane fire actuator as claimed in any one of claims 2 to 6; The barrel of the rotary blade type fire working actuator forms a wing root / inner wing; The rotor of the rotary vane type pyrotechnic actuator is fixedly connected to the airfoil.

8. The integrated airfoil according to claim 7, characterized in that: The airfoil is formed by an outer wing.

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