459results about "Turn-sensitive devices" patented technology

Microelectromechanical component (100) for motion measurement, comprising: a fortified section (118); a single, central anchor (106) coupled to the attached section (118) with four sides; a first non-straight suspension element (108) coupled to the anchor (106) on one side of the anchor (106); a second non-straight suspension member (120) coupled to the anchor (106) on the same side of the anchor (106), wherein the second non-straight suspension member (120) has a shape and position that mirrors the first non-straight suspension member (108) on a plane (122) bisecting the anchor; and a test mass (104) which is planar, wherein the test mass (104) is suspended at least partially on the first non-straight suspension member (108) and the second non-straight suspension member (120) such that the test mass (104) is rotatable about the anchor (106) and displaceable in a plane which is parallel to the attached section (118), where the first and second non-straight suspension members (108, 120) are bending bearings, wherein the first non-straight suspension member (108) has a C-shape, wherein the C-shape includes an inner section (110) which is coupled to the anchor (106) and extends towards the plane (122) bisecting the anchor, a central section (114) which includes a nearby section and has a distant section, whereby the near section is coupled to the inner section (110), and the far section extends away from the anchor (106) along the plane (122) bisecting the anchor and is coupled to an outer section (112) extending away from the plane (122) bisecting the anchor.

Solid-state platforms based on electro-nuclear spin systems are attractive candidates for rotation sensing due to their excellent sensitivity, stability, and compact size, compatible with industrial applications. Conventional spin-based gyroscopes measure the accumulated phase of a nuclear spin superposition state to extract the rotation rate and thus suffer from spin dephasing. A gyroscope protocol based on a two-spin system that includes a spin intrinsically tied to the host material, while the other spin is isolated. The rotation rate is then extracted by measuring the relative rotation angle between the two spins starting from their population states, robust against spin dephasing. In particular, the relative rotation rate between the two spins can be enhanced by their hyperfine coupling by more than an order of magnitude, further boosting the achievable sensitivity.

Various optical systems for use in a light pulse atomic interferometer (LPAI)-based one-, two-, or three-axis accelerometer or gyroscope are disclosed. As an LPAI accelerometer or gyroscope may employ many different laser beams to implement the LPAI functionality, ways of combining these different laser beams to thereby simplify the optical systems are desired. The cooling laser beam portion of the optical system may be simplified using one or more reflective grating chips. The Raman laser beam optics may be simplified using combiners and separators. For LPAI systems sensing along three axes, various optical switching schemes may be employed, including ones that generate variable data-rates with a primary sensing axis having a higher data-rate than the secondary sensing axes. Further, by combining various laser beams in a time-multiplexed manner, the number of optical fiber tethers to a sensor head may be reduced.

An adjuster performs simultaneous irradiation of M laser beams to an atomic beam, where M is a predetermined integer satisfying 3≤M. The course of each of the M laser beams intersects with the course of the atomic beam. A component, in a direction perpendicular to the course of the atomic beam, of the sum of radiation pressure vectors that the M laser beams respectively have is zero. A component, in a direction of the course of the atomic beam, of the sum of the radiation pressure vectors that the M laser beams respectively have is negative for atoms having speeds greater than a predetermined speed, and positive for atoms having speeds smaller than the predetermined speed.

The invention belongs to the field of inertial navigation measurement, and discloses a nuclear magnetic resonance gyroscope main magnetic field control method and system based on active disturbance rejection control, and the method comprises the following steps: establishing a nuclear magnetic resonance gyroscope main magnetic field system differential equation; designing an active-disturbance-rejection controller based on a differential equation of a main magnetic field system of the nuclear magnetic resonance gyroscope; based on an active-disturbance-rejection controller, a nuclear magnetic closed-loop system is built in combination with a gyro prototype, and main magnetic field disturbance is restrained. The invention particularly provides a magnetic field control method based on linear active disturbance rejection control (LADRC) aiming at the key influence of the stability of a main magnetic field in a nuclear magnetic resonance gyroscope on the system output precision, which is used for solving the problems of insufficient control precision and poor robustness in the face of system disturbance, model uncertainty and nonlinear environment influence of the existing PID control method. Therefore, the zero-bias stability and the measurement precision of the nuclear magnetic resonance gyroscope are improved.

An optical frequency generation system (100), comprising: - reference atoms (7) in a gas phase, - an interrogation laser source (1) configured to emit an interrogation signal (101) comprising a first optical frequency suitable for exciting a two-photon transition in said reference atoms (7), said interrogation signal (101) being configured to interact with said reference atoms (7) in a Doppler-free scheme; - optical frequency modulation means (31, 31a, 31b) configured to adjust said first optical frequency and to modulate said first optical frequency at a first modulation frequency f1; - an optical sensor (9) configured to detect a fluorescence signal (110) from said reference atoms (7); - a first control loop (10) configured to lock said first optical frequency to a resonance frequency of said two-photon transition, said fluorescence signal (110) being input into the first control loop (10); - a mitigation laser source (2) configured to emit a mitigation signal (102) comprising a second optical frequency selected to produce a light-shift of said two-photon transition of opposite sign of the light-shift produced by the interrogation signal (101); characterized in that the optical frequency generation system (100) further comprises: - optical amplitude modulation means (5) configured to modulate the amplitude of the interrogation signal (101) and of the mitigation signal (102) at a second modulation frequency f2, and - a second control loop (20) configured to adjust the relative amplitude of the mitigation signal (102) with respect to the interrogation signal (101) such as to cancel the effective light-shift of the combined interrogation (101) and mitigation (102) signals.

The invention relates to a hemispherical resonator and hemispherical gyroscope parameter and defect identification system and method, and belongs to the technical field of hemispherical resonator gyroscopes. According to the invention, automatic identification of damping non-uniformity, rigidity non-uniformity and 1-3-order quality defect parameters is respectively carried out on the fused quartz hemispherical resonator before and after film coating and the gyroscope header after base assembly, so that the full-flow coverage test of the hemispherical resonator gyroscope is realized; various parameters are identified in the whole process from harmonic oscillator machining forming to the gauge outfit state, the testing precision, the system reusability, the operation convenience and consistency are greatly improved, and the production efficiency is improved.

A three-axis angular rate sensor with a substrate and a A double rotor is proposed, wherein the double rotor has a first and a second rotor (1, 2) which are elastically connected to one another via a first coupling element (8) in such a way that the two rotors (1, 2) can be excited to antiphase torsional vibrations, wherein the first rotor (1) has a first and a second second seismic mass (3, 4) which are mounted so as to be deflectable relative to the first rotor (1) and the second rotor (2) has a third and a fourth seismic mass (5, 6) which are mounted so as to be deflectable relative to the second rotor (2), wherein the first mass (3) is connected to the third mass (5) via a first rocker element (9) is connected in such a way that the third mass (5) at a lateral deflection of the first mass (3) is deflected in an opposite lateral direction, wherein the second mass (4) is connected to the fourth mass (6) via a second rocker element (9') such that the fourth mass (6) is deflected in an opposite lateral direction upon a lateral deflection of the second mass (4).

The invention discloses an SERF atomic gyro signal detection device and method based on an optical heterodyne method, and belongs to the technical field of atomic polarization stability control, after magnetic fields with x-axis frequency and y-axis frequency are applied to atoms in a sensitive unit air chamber, x-axis electron polarizability information under respective modulation frequencies comprises longitudinal polarizability information and longitudinal magnetic field information, and x-axis electron polarizability information and y-axis electron polarizability information under respective modulation frequencies comprise longitudinal polarizability information and longitudinal magnetic field information; the value of the longitudinal polarizability is obtained by resolving information contained in the two, and effective longitudinal polarizability closed-loop control is achieved through a liquid crystal phase delayer power stabilizing rate system. Based on the biaxial magnetic field modulation technology, interference of longitudinal magnetic field fluctuation on polarizability closed-loop control is effectively avoided, and effective polarizability in-situ closed-loop control is achieved.

A compact grating-mirror magneto-optical trap (GMOT) cold atom inertial sensor head is disclosed. To make the sensor head compatible with the high vibration levels encountered in dynamic environments, the number of optical ports in the vacuum chamber is minimized and various components, including fixed optical components and a reflective grating chip, are hard mounted within the vacuum chamber. The use of the reflective grating chip reduces the number of optical ports required for cooling beams from six to one. The number of optical ports is further reduced by time multiplexing multiple beams passing through a given optical port.

The invention relates to the technical field of MEMS, and discloses an MEMS gyroscope closed-loop driving loop, a phase-locked loop circuit outputs a synchronous clock signal, and a clock generation circuit is used for performing gate logic operation, frequency division and layered delay addition on the synchronous clock signal to generate multiple groups of collaborative non-overlapping clock signals; a band-pass delta-sigma modulator, a CV conversion circuit and a digital signal processing module are controlled; meanwhile, through phase locking of a synchronous clock phase, a main sampling switch signal is synchronized with a falling edge of the synchronous clock phase, and the sampling phase is ensured to be 0 degree, so that a digital code stream signal of which the sampling phase is kept at 0 degree is output, and the sampling phase of the band-pass delta-sigma modulator is strictly synchronized with the mechanical vibration phase of the MEMS gyroscope; and phase deviation in the driving loop is eliminated. The digital signal processing module adjusts the amplitude and the phase of a feedback signal of the whole driving loop, so that the stability and the adjustability of the driving loop are improved under the condition that the MEMS gyroscope is driven under a proper condition.

The invention discloses a holosymmetric four-mass MEMS gyroscope which comprises four sensitive mass block coupling structures which are arranged in a central symmetry manner, and four first U-shaped beams, four n-shaped beams and a cross-shaped coupling structure which are arranged in a central symmetry manner and are connected with the four sensitive mass block coupling structures, compared with the prior art, the four sensitive mass block coupling structures are designed compactly and symmetrically, so that the sensitivity can be effectively improved, and thermally induced drift can be effectively reduced. The driving mode and the working mode are separated through the specific coupling mechanism, so that frequency coupling is avoided, and environmental vibration interference is reduced. And meanwhile, the symmetry of the structure is beneficial to uniform distribution of thermal stress or mechanical stress, so that zero drift caused by temperature change is inhibited.

A gyroscopic sensor system can include a proof mass, which can be configured to vibrate in a first primary mode and a second primary mode, where the first primary mode can be driven into resonance, where an in-phase signal can be induced in the second primary mode in response to a rotation of the gyroscopic sensor system. The gyroscopic sensor system can also include a quadrature force circuit, which can be configured to force the second primary mode of the proof mass. The gyroscopic sensor system can also include control circuitry, which can be configured to drive the quadrature force circuit using a quadrature test signal which can be configured to generate a quadrature response in the proof mass that can be in quadrature with the in-phase signal. The control circuitry can also be configured to measure the quadrature response of the proof mass to the quadrature test signal.

The application belongs to the field of optical precision manufacturing, and relates to a bottom-up atomic gas chamber manufacturing device and manufacturing method. The device is composed of a vacuum cavity, a pumping pipeline, a gas inlet pipeline, a discharge electrode plate set, an insulating support, a gas chamber, a laser, an alkali metal source and a vacuum gauge. The device is used for manufacturing the atomic gas chamber from bottom to top, and can be used for preparing various gas chambers with different gas pressure ratio requirements, thereby helping to realize customized preparation. The device reduces the disadvantages of impurity adsorption on the inner wall of the gas chamber and reduces uncontrollable risks. The device has high integration, high preparation efficiency and large secondary development space, and is favorable for accelerating the technical iteration of the atomic gas chamber and the cross-generation development of key technologies such as nuclear magnetic resonance gyroscopes, atomic clocks and magnetometers.

The present disclosure is directed to a device configured to detect whether the device is in a bag or outside of the bag. The device determines whether the device is in or outside of the bag based on distance measurements generated by at least one proximity sensor and motion measurements generated by at least one motion sensor. By using both distance measurements and motion measurements, the device is able to detect whether the device is in the bag or outside of the bag with high accuracy and robustness.

A high-temperature tank (116) includes an optical window which transmits a laser (132) and is provided at one end, and a right-angle conical mirror (102) which is provided at the other end, has an opening (106) at the apex and which reflects laser light (132) incident from the optical window towards the one end in an area other than the opening (106). A magnetic field generator (112) generates a magnetic field in the region of intersection of the laser reflected by the right-angle conical mirror (102). A magnetic field gradient relaxation module (130) generates a relaxation magnetic field which relaxes the gradient of the magnetic field generated by the magnetic field generator (112).

A vibration-type angular velocity sensor (100) includes a primary side control circuit (2) and a secondary side control circuit (3) which are configured so that a function as the primary side control circuit (2) and a function as the secondary side control circuit (3) are interchangeable, in which an offset value after interchange and an offset value before interchange are symmetric values with respect to a predetermined reference value.

To provide a sensor modules, etc. that can prevent degradation of angular velocity and acceleration detection accuracy caused by noise.SOLUTION: A sensor module 10 includes: an X-axis angular velocity sensor device 30X for outputting digital X-axis angular velocity data; a Y-axis angular velocity sensor device 30Y for outputting digital Y-axis angular velocity data; a Z-axis angular velocity sensor device 30Z for outputting digital Z-axis angular velocity data; an acceleration sensor device 40 for outputting digital X-axis, Y-axis, and Z-axis acceleration data; a microcontroller 80; a first digital interface bus BS1 for electrically connecting the X-axis angular velocity sensor device 30X, the Y-axis angular velocity sensor device 30Y, the Z-axis angular velocity sensor device 30Z, and a first digital interface 83; and a second digital interface bus BS2 for electrically connecting the acceleration sensor device 40 and a second digital interface 84.SELECTED DRAWING: Figure 1

The invention relates to gyroscope quadrature and phase error estimation and correction. A method includes generating a signal using a gyroscope. The generated signal includes a Coriolis component and a quadrature component. A signal generated by the gyroscope is demodulated using a feedback loop, generating a demodulated signal. The demodulation includes generating an in-phase demodulated signal, and demodulating the gyroscope-generated signal using the generated in-phase demodulated signal. The in-phase demodulated signal includes a phase modulated signal, and the demodulated signal includes a frequency component corresponding to the phase modulated signal. An amplitude of a frequency component corresponding to the phase modulated signal in the demodulated signal is estimated, and the feedback signal is generated based on the estimated amplitude of the frequency component corresponding to the phase modulated signal. Compensation of the quadrature component of the gyroscope-generated signal is applied based on the feedback signal. An output signal is generated based on the demodulated signal.

A kind of atomic gyroscope pumping rate stable composite control method based on phase reshaping extended state observer and power approaching sliding mode control.Aiming at the problems that standard linear extended state observer has steady-state estimation error under the action of ramp disturbance, disturbance estimation phase lag and it is difficult to balance between observation bandwidth improvement and noise sensitivity, a composite corrector composed of lead network and lag network is cascaded at the output end of disturbance estimation of extended state observer, the disturbance estimation channel is shaped in frequency domain, phase lead is provided in mid-frequency band to reduce compensation delay, amplitude lag characteristic is used to suppress high-frequency noise, and parameter constraint design is used to realize zero-error estimation of ramp disturbance;At the same time, a power approaching sliding mode controller is constructed to improve the adaptability to the nonlinear, internal and external coupling and parameter uncertainty of atomic gyroscope system, and the phase reshaping extended state observer is combined to effectively estimate and feed forward compensate the lumped disturbance, so as to improve the stability and accuracy of pumping rate control.The present application can balance dynamic anti-disturbance performance, steady-state control accuracy, convergence speed and noise robustness without significantly improving the observation bandwidth, and is suitable for atomic gyroscope precision control system affected by ultra-low frequency slowly varying disturbance.

The invention relates to the technical field of gyroscopes, and discloses a frequency hopping gyroscope, which comprises a first connecting switch, a second connecting switch, a first driving comb tooth electrode and a second driving comb tooth electrode, when the angular velocity in the first direction is detected, the two driving mass blocks are switched between two driving modes of same-direction driving motion and reverse-direction driving motion, and when the angular velocity in the third direction is detected, the two detection mass blocks are switched between two detection modes of same-direction detection motion and reverse-direction detection motion; and the second connection switch is configured to be capable of changing the polarities of the first detection comb tooth electrode and the second detection comb tooth electrode of the detection electrodes on the detection mass block with the detection direction changing. According to the frequency hopping gyroscope disclosed by the invention, the problem that the existing gyroscope generally adopts a fixed working frequency is solved, the working frequency of the gyroscope can be changed, and the frequency hopping gyroscope has relatively high safety performance.

A three-axis rotation rate sensor. The sensor includes a substrate and a double rotor including a first rotor and a second rotor elastically connected to each other via a first coupling element such that the two rotors are excitable to antiphase rotary oscillations, the first rotor including a first and a second seismic mass, which are deflectably mounted vis-à-vis the first rotor and the second rotor includes a third and a fourth seismic mass, which are deflectably mounted vis-à-vis the second rotor, the first mass being connected to the third mass via a first rocker element such that the third mass is deflected in an opposite lateral direction upon a lateral deflection of the first mass, the second mass being connected to the fourth mass via a second rocker element such that the fourth mass is deflected in an opposite lateral direction upon lateral deflection of the second mass.

The application relates to the technical field of lasers, in particular to a semiconductor laser for a quantum gyroscope and a preparation method thereof. The semiconductor laser for the quantum gyroscope comprises a stacking structure, the stacking structure comprises an N-type substrate, an N-type cladding layer, an N-type waveguide layer, an active region, a first P-type waveguide layer and a waveguide structure which are stacked in a first direction in sequence, and the waveguide structure comprises a low-duty-cycle V-shaped groove grating, a multimode interference coupling beam splitting waveguide, a gain waveguide array, a multimode interference coupling beam combining waveguide, a high-duty-cycle V-shaped groove grating and a micro-tapered waveguide which are arranged and connected in a second direction in sequence. The application is favorable for realizing the semiconductor laser for the quantum gyroscope with high power and narrow linewidth under the premise of reducing the complexity of the device structure.

The present invention discloses a gas chamber temperature control method for a SERF inertial measurement device based on second harmonic generation. The method utilizes gas chamber optical depth information obtained by the SERF device's own detection system to perform feedback regulation on the laser heating power of the atomic gas chamber, thereby achieving real-time and stable control of the atomic density or temperature in the gas chamber. This avoids the magnetic field interference introduced by the use of thermal resistors as temperature sensors in existing solutions, thereby achieving truly non-magnetic, all-optical gas chamber heating and its control system, and helping to improve the sensitivity of the SERF inertial measurement device.

The invention discloses a miniaturized pumping optical module based on a VCSEL (Vertical Cavity Surface Emitting Laser), which can realize miniaturization of the optical module through optical element layout and low-stress and less-stray-light installation, thereby being beneficial to meeting the requirements of performance test and pursuing of ultrahigh sensitivity by a large scientific device, and is characterized in that the miniaturized pumping optical module comprises a shell, the shell is formed by overlapping a photosensitive resin lower-layer structure shell, a photosensitive resin middle-layer structure shell and a photosensitive resin upper-layer structure shell layer by layer, a large gear and a small gear are arranged on the top face of the upper-layer structure shell, and a cylindrical groove where a quarter-wave plate is embedded is formed in the inner wall face of a center hole of the large gear. A VCSEL laser and a photoelectric detector which are parallel are arranged on the top face of the lower-layer structure shell, a polarization splitting prism is arranged in the upper-layer structure shell, a collimating lens set formed by overlapping a concave lens and a convex lens is arranged in a light source channel in the middle-layer structure shell, the transmission side of the polarization splitting prism is aligned with the quarter-wave plate, and the transmission side of the collimating lens set is aligned with the quarter-wave plate. The reflection side of the polarization splitting prism is connected with a photoelectric detector.

Method for the precise measurement operation of a micromechanical angular rate sensor, comprising at least one deflectably suspended seismic mass (1, 15, 20), at least one drive device for driving the seismic mass (1, 15, 20) and at least one first (2, 11, 18) and one second (3, 12, 19) trim electrode element, which are directly or indirectly jointly assigned to the seismic mass (1, 15, 20), wherein a first electrical trim voltage (U) is applied between the first trim electrode element (2, 11, 18) and the seismic mass (1, 15, 20). TO1 , U TLO1 , U TRO1 , U TU2 , U T1H , U T2V ) and a second electrical trim voltage (U) between the second trim electrode element (3, 12, 19) and the seismic mass (1, 15, 20) TO2 , U TLO2 , U TRO2 , U TU1 , U T2H , U T1V) are set, whereby the first and second electrical trim voltages depend at least on a quadrature parameter (U). T ) and a resonance parameter (U f ) are set, characterized by the fact that the first (U TO1 , U TLO1 , U TRO1 , U TU2 , U T1H , U T2V ) and the second (U TO2 , U TLO2 , U TRO2 , U TU1 , U T2H , U T1V ) electrical trim voltage is set so that the sum of the square of the first electrical trim voltage (U) TO1 , U TLO1 , U TRO1 , U TU2 , U T1H , U T2V ) multiplied by a first constant factor (α) and from the square of the second electrical trim voltage (U) TO2 , U TLO2 , U TRO2 , U TU1 , U T2H , U T1V) multiplied by a second constant factor (β), is kept constant and / or is based on a first reference value of the resonance parameter (U) f ) is set to the square.

The utility model provides a miniature shock-resistant gyroscope, which belongs to the technical field of angular rate, and comprises an assembly shell, a sealing cover, a detection component and a shock absorption piece, the assembly shell is provided with a containing cavity, and one side of the containing cavity is provided with an opening communicated with the outside; the sealing cover covers the opening of the accommodating cavity and is connected to the assembly shell; the detection assembly is arranged in the accommodating cavity, and the detection assembly comprises a packaging shell and a detection part arranged in the packaging shell; and the damping part sleeves or surrounds the periphery of the packaging shell and is used for relieving the vibration force borne by the detection assembly. The utility model provides a miniature shock-resistant gyroscope, and aims to solve the problems that a miniature gyroscope in the prior art has higher sensitivity to environmental interference and is easily influenced by an external vibration environment, so that the detection precision is reduced.

The vibration-type angular velocity sensor (100) is provided with a phase synchronization circuit (26) that outputs a frequency signal for controlling the frequency of a drive signal input to the vibrator (10). A phase synchronization circuit (26) includes: a comparator (41) that compares a detection signal from an oscillator (10) with a reference signal generated from a frequency signal; an integrator (42) having an operational amplifier (50) and a capacitor (70) and outputting an integrator output signal on the basis of the output from the comparator (41); an oscillator (43) that outputs a frequency signal of a predetermined frequency on the basis of the integrator output signal from the integrator (42); and a short-circuit switch unit (44) that, when the oscillator (10) is activated, is short-circuited so as to bypass the capacitor (70) of the integrator (42).

The application belongs to the technical field of precision measurement, and discloses a heating, excitation and frequency splitting measurement method of a quartz hemispherical resonator. The method uniformly heats the quartz hemispherical resonator by using an infrared light source, excites the quartz hemispherical resonator based on a "four-wave belly" vibration mode by a piezoelectric excitation sheet, reads vibration signals by a laser vibration tester, analyzes the frequency splitting and the direction of the stiffness uneven axis of the quartz hemispherical resonator, and adjusts the stiffness unevenness of the quartz hemispherical resonator by etching and removing weight by an ion beam. The method solves the problem of the circumferential stiffness unevenness of the quartz hemispherical resonator, and compared with the previous frequency splitting adjustment of the resonator, the application adjusts the frequency splitting of the resonator from the stiffness adjustment angle, and improves the frequency splitting temperature change interference characteristic of the quartz hemispherical resonator after adjustment.

Micromechanical structure (1), in particular a gyroscope, comprising a substrate (2) having a principal extension plane (100), a first detection mass element (11) and a second detection mass element (21), wherein the first detection mass element (11) is provided to be excitable by a first drive element (10) to a first vibration (101) parallel to the principal extension plane (100), wherein the second detection mass element (21) is provided to be excitable by a second drive element (20) to a second vibration (201) antiparallel to the first vibration (101), wherein a first Coriolis deflection of the first detection mass element (11) along a third direction (Z) perpendicular to the principal extension plane (100) is detectable by a first detection means,wherein a second Coriolis deflection of the second detection mass element (21) along the third direction (2) is detectable by a second detection means and wherein the first and the second detection mass elements (11, 21) are coupled to each other by means of a first coupling element (3), characterized in that the first detection mass element (11) is designed as a first rocker structure (11') and the second detection element (21) as a second rocker structure (21'), wherein the first and second rocker structures (11' and 21') are attached to the first and second drive elements (10 and 20) by means of a first and second torsion spring (13 and 23, respectively), respectively, wherein the first and second torsion axis (13' and 23') of the first and second torsion spring (13, 23) are parallel to the first and second directions (X, 2, 3, 4, 5, 6, 7, 8, 9, 10 ...Y) is provided and the first or second rocker structure (11' or 21') has an asymmetric mass distribution with respect to the first or second torsion axis (13' or 23'), wherein the first and / or the second torsion spring (13, 23) are designed as a conductor spring, wherein the first and / or the second torsion spring (13, 23) are designed as a double conductor spring.