Folding pneumatic rocket rudder
By combining cylindrical torsion bars and spring-loaded clamps, the shortcomings of foldable aerodynamic rocket control surfaces in terms of thermal protection and stiffness are solved, enabling reliable deployment and locking under high-load environments and improving the compactness and reliability of rocket control surfaces.
Patent Information
- Application Number
- CN202480015773.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2023-03-29
- Filing Date
- 2024-03-22
- Publication Date
- 2025-11-07
AI Technical Summary
Existing foldable aerodynamic rocket control surface structures are inadequate in terms of thermal protection and rigidity, and their deployment torque is insufficient, which limits their application.
A cylindrical torsion bar is used as the mechanical deployment drive mechanism. Combined with a spring-loaded clamp and a locking structure, reliable locking is achieved through the cooperation of the rotating component and the wing platform hole, eliminating the problems of reduced control surface stiffness and thermal protection.
It achieves reliable deployment and locking of the control surfaces during rocket launch and high-speed flight, improving the compactness and reliability of the control surface structure and adapting to high-load environments.
Smart Images
Figure CN120917285A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present invention relates to the field of rocket technology and concerns a foldable aerodynamic surface and its deployment locking mechanism. BACKGROUND
[0002] A known foldable aerodynamic trajectory correction mechanism (see patent RU 2 280 230 C1 "Foldable aerodynamic trajectory correction mechanism", publication date July 20, 2006). The foldable aerodynamic trajectory correction mechanism comprises a surface, a trunnion, a folding shaft, a spring and a clamping device. The surface is provided with a recess in which the trunnion with a shaft is installed. On both sides of the surface along the longitudinal axis of the surface and the trunnion there are spring-loaded clamping devices with a terminal conical part and a folding shaft with a spring. The spring of the folding shaft is connected to the surface at one end and to the trunnion at the other end.
[0003] As the closest analogue of the technical solution adopted in the present invention, the foldable aerodynamic rocket rudder was chosen as the prototype (see patent RU 2 535 789 C1, IPC classification F42B 10 / 14, publication date December 20, 2014 "Foldable aerodynamic rudder", August 2, 2013). The surface of the rudder uses a helical cylindrical spring to transmit rotational motion from the root of the surface to the folding part to create a deployment torque, the spring is installed on the rotation axis of the folding part; as a locking mechanism, two spring-loaded stops are installed in the special elements of the root of the surface and hold the surface in the folded state by means of the spring-loaded stops.
[0004] The disadvantages of this technical solution are as follows: the complex root part of the surface extending along the lateral chord length reduces the stiffness of the surface; there are through holes for stops in the leading edge of the root part of the surface, which is the most heat-loaded part; and the deployment torque provided by the helical cylindrical spring is relatively low, which limits the application.
[0005] The technical problem solved by the present invention is to create a compact and reliable structure of a foldable aerodynamic surface of a rocket, which, in combination with a thermal protection system, is capable of withstanding all loads from the launch of the rocket to the arrival at the target at subsonic and hypersonic speeds. SUMMARY
[0006] The foldable aerodynamic rocket rudder is composed of a root part and a rotating part connected by a tubular rotation axis. A cylindrical torsion bar is used as a mechanical deployment drive mechanism for the rotating part of the foldable aerodynamic rocket rudder. The torsion bar is fixed at both ends to the root part and the rotating part of the foldable aerodynamic rocket rudder. In the root part of the foldable aerodynamic rocket rudder there is a locking mechanism for the rotating part, and in the rotating part there is a corresponding hole for the locking catch to be inserted into.
[0007] The technical effect is achieved by using a spring-loaded clamp, which is embedded in the wing platform of the folded aerodynamic rocket rudder root member through a connecting piece and a threaded nut, so that additional spring-loaded stoppers and guide slopes in the shear force concentration area are not needed, and a circular cross-section torsion bar deployment mechanism is used as a driving device.
[0008] The technical effect of the deployment and locking of the folded aerodynamic rocket rudder is achieved by the following means: the rotating part obtains rotational motion by obtaining the kinetic energy generated by the torsion of the cylindrical torsion bar, and when the tensioning rod with a threaded nut is sheared, the rotating part collides with the rudder root member, and the clamp is released under the action of the compression spring and enters the wing platform hole. The spring-loaded lock, which is fixed by a connecting piece and released when the chord plane of the rotating part coincides with the axis of symmetry of the wing platform, is combined with the conical guide part of the lock and the conical hole structure of the wing platform to ensure the reliable locking of the aerodynamic rudder. BRIEF DESCRIPTION OF DRAWINGS
[0009] The present application is illustrated by the following drawings: Figure 1 The overall schematic diagram of the folded aerodynamic rocket rudder in the deployed state is shown. Figure 2 The view of the folded aerodynamic rocket rudder in the deployed state is shown. Figure 3 The cross-sectional view of the folded aerodynamic rocket rudder in the deployed state along the chord plane is shown. Figure 4 The schematic diagram of the folded aerodynamic rudder is shown. Figure 5 The cross-sectional view of the folded aerodynamic rocket rudder root member with a locking mechanism in the folded state is shown.
[0010] The folded aerodynamic rocket rudder Figure 1 ) includes a root member 1 and a rotating part 2. The root member of the folded aerodynamic rocket rudder includes a wing platform 3 Figure 1 ) and a rotating shaft 4 Figure 2 ). Two mutually parallel coaxial holes are provided on the root member and the rotating part. The fixed rotating shaft 5 of the rotating part of the folded aerodynamic rocket rudder is fixed on the wing platform 3 by a screw 17 and is installed in the hole 19 Figure 3 ). In the fixed rotating shaft 5, a cylindrical torsion bar 6 with a hexagonal end is provided, and the other end of the torsion bar is pre-torsioned in the folding direction of the rocket aerodynamic rudder and is fixed in the rotating part 2 by a clamp 18. The rotating part 2 is deployed from the folded position Figure 4 ) to the open position Figure 2 ) by the elastic force of the torsion bar 6, one end of which is fixed in the fixed shaft 5 connected to the wing platform 3 of the root member 1, and the other end is fixed in the rotating part 2. The prepositioning of the locking mechanism of the rotating part of the folded aerodynamic rocket rudder is completed through the hole 20.
[0011] The rotating member locking mechanism is located in the wing platform 3 of the folding pneumatic rocket rudder root member 1, and includes the locking catch 7 and 8, the thrust bushing 9 of the locking catch 7, the thrust bushing 10 of the locking catch 8, the compression springs 11 and 12, and the connecting member 13. The connecting member 13 is composed of a cylindrical rod 14, a shear threaded cylindrical nut 15, and a bushing 16 mounted by adhesive. DETAILED DESCRIPTION
[0012] The folding pneumatic rocket rudder deployment process is as follows: the rotating member 2 is deployed from the folded position ( Figure 4 ) to the open position ( Figure 2 ) about the fixed shaft 5 under the elastic force of the torsion bar 6, and this position is co-linearly continued with the root member 1. When the rotating member 2 collides with the shear threaded cylindrical nut 15 of the stop connecting member, the nut is sheared and the locking catch 7 and 8 are released, the compression springs 11 and 12 are extended and push the locking catch 7 and 8 into the corresponding holes of the rotating member 2, so that the rotating member 2 is fixed in the root member 1.
[0013] The folding pneumatic rocket rudder design has completed the entire ground and flight test cycle, and is currently being applied to the export air defense missile system.
Claims
1. A folding pneumatic rocket rudder comprising a rotating part and a root member, a cylindrical torsion bar and a locking mechanism comprising a compression spring and a lock, characterized in that: The root member of the folding pneumatic rocket rudder is composed of a wing platform and a rotating shaft; the rotating part has two mutually parallel coaxial holes on the wing platform of the root member, the fixed rotating shaft of the folding pneumatic rudder rotating part is installed in the upper hole and fixed to the wing platform through a screw; the cylindrical torsion bar is fixed to the fixed rotating shaft through a hexagonal end; the other end of the torsion bar is pre-twisted to the folding direction of the pneumatic rocket rudder and connected to the rotating part through a tap wrench; the lower hole arranged on the rotating part is used for presetting the locking mechanism of the rotating part, the locking mechanism of the rotating part is arranged in the hole of the wing platform of the root member and comprises a lock catch, a thrust bushing of the lock catch, a compression spring and a connecting piece, the connecting piece is composed of a cylindrical rod, a shearing threaded cylindrical nut and a bushing adhesively installed, and the locking part of the lock catch and the hole in the wing platform are both conical.